CN112069603B - Nozzle inlet non-uniform flow parameter reconstruction method, device, medium and equipment - Google Patents
Nozzle inlet non-uniform flow parameter reconstruction method, device, medium and equipment Download PDFInfo
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Abstract
The invention discloses a method, a device, a medium and equipment for reconstructing non-uniform flow parameters of a nozzle inlet, wherein the method comprises the following steps: s1, dividing calculation grids aiming at the spray pipe, and determining the flow field parameter form on each grid point; s2, obtaining the wall pressure of the spray pipe and forming a vector; s3, determining an observation matrix H according to the wall pressure measuring point position of the spray pipe and the calculation grid; s4, giving the distribution form of the Mach number and the pressure of the nozzle inlet according to a polynomial form; s5, sampling according to the initial estimation range of the quantity E to be estimated at the inlet of the spray pipe by the given number N of sampling points; s6, according to different combinations of parameters E to be estimated of the nozzle inlets, calling fluid calculation software to carry out nozzle flow field solution; s7, correcting the parameter to be estimated of the nozzle inlet; and S8, iterating the parameters to be estimated of the corrected nozzle inlet, and calculating to obtain the nozzle flow field parameters corresponding to the wall pressure of the nozzle. The invention can realize accurate and rapid reconstruction of the nonuniform flow parameters at the nozzle inlet.
Description
Technical Field
The invention relates to the technical field of supersonic velocity spray pipe flow fields, in particular to a method, a device, a medium and equipment for reconstructing nonuniform flow parameters of a spray pipe inlet.
Background
The nozzle 2 of the existing scramjet engine is positioned at the tail part of an aircraft 1, is a core thrust component of the aircraft 1 and directly forms aircraft thrust, and the nozzle inlet 3 is connected with a combustion chamber 4 (see fig. 1). The design of the jet pipe of the scramjet engine directly depends on jet pipe inlet parameters, the influence of the parameters such as jet pipe inlet Mach number, pressure and the like on the jet pipe profile and the thrust performance of the jet pipe is obvious, and inaccurate jet pipe inlet parameters are also important reasons for causing the thrust loss of the jet pipe. Accurate determination of nozzle inlet parameters is of great significance in improving aircraft performance.
Because the inlet temperature of the scramjet engine spray pipe is high, the speed is high, and certain non-uniformity exists in inlet parameters, the direct measurement difficulty is high, and an effective measurement means is not available. At present, the determination of the inlet parameters of the spray pipe mainly depends on rough thermodynamic estimation, the accuracy of the determination of the inlet parameters is low, the matching of the molded surface of the spray pipe and the outlet parameters of a combustion chamber is seriously influenced, and the thrust loss of the spray pipe is large.
Therefore, the main problems of the existing nozzle inlet parameter determination method are that: the parameters of the nozzle inlet depend on one-dimensional engineering estimation, the distribution of Mach number and pressure at the nozzle inlet cannot be provided, and the optimal design of the nozzle profile is seriously influenced.
Disclosure of Invention
The invention provides a method for reconstructing non-uniform flow parameters of a nozzle inlet, which aims to solve the technical problems that the prior nozzle inlet parameters depend on one-dimensional engineering estimation, the distribution of Mach number and pressure at the nozzle inlet cannot be provided, and the optimal design of the nozzle profile is seriously influenced.
The technical scheme adopted by the invention is as follows:
a nozzle inlet non-uniform flow parameter reconstruction method comprises the following steps:
s1, dividing calculation grids aiming at the jet pipe, and writing the flow field parameter on each grid point as xi i ＝(ρ i ,u i ,p i ) Where the subscript i denotes a certain grid point, ρ i Denotes the density, u, of grid points i i Representing the x-direction velocity component, p, at a certain grid point i i Represents the pressure at grid point i;
s2, measuring and obtaining the wall pressure of the spray pipe, and forming a vector Y (p) according to the wall pressure data of the spray pipe 1 p 2 p 3 … p l ) T Wherein the subscript l represents the number of pressure measurement points, and T represents the matrix transposition;
s3, determining an observation matrix H according to the wall pressure measuring point position of the spray pipe in the test and the calculation grid;
s4, giving the distribution form of the Mach number and the pressure of the nozzle inlet according to a polynomial form, and obtaining a parameter E to be estimated of the nozzle inlet according to the polynomial;
s5, setting the number N of sampling points, sampling in the initial estimation range of the parameter E to be estimated at the inlet of the given spray pipe, determining the initial sample set of the inlet parameter, wherein the combination of the parameters E to be estimated at the inlet of different spray pipes corresponds to different inlet Mach numbers and pressure distribution forms;
s6, according to different combinations of parameters E to be estimated of the nozzle inlets in the initial sample set, calling fluid calculation software to carry out nozzle flow field solution, obtaining the speed, density and pressure distribution of the flow field, and obtaining a matrix X containing state vectors of all samples f ＝(x f(1) x f(2) … x f(N) ) Wherein:
x f ＝(ξ 1 ,ξ 2 ,…,ξ i ,…,ξ m ,E) T for the state vector corresponding to the combination of the parameter E to be estimated at the inlet of each spray pipe, the subscript m represents the number of grid points, and the superscript f represents the state of the flow field obtained by calculating the flow field;
s7, correcting the initial parameter to be estimated of the nozzle inlet;
and S8, generating a nozzle inlet Mach number and a pressure profile based on the corrected nozzle inlet parameter to be estimated, iterating again, and repeating the steps S6-S7 until the difference between the nozzle inlet parameter to be estimated and the last iteration step is smaller than a set threshold value, and calculating to obtain a nozzle flow field parameter corresponding to the nozzle wall surface pressure according to the converged nozzle inlet parameter to be estimated.
Further, in step S3, when the observation matrix H is determined according to the wall pressure measurement point position of the nozzle wall and the calculation grid in the test, the element value of the observation matrix H corresponding to the position where the wall pressure measurement point position coincides with the calculation grid point or the distance is smaller than the set threshold is 1, otherwise, the element value of the observation matrix H is 0.
Further, the distribution form of the mach number and the pressure at the nozzle inlet given according to the polynomial form is specifically as follows:
the parameter E to be estimated of the nozzle inlet comprises M e 、n 1 、P 0,e 、c 2 And n 3 Wherein, M is e Representing the nozzle inlet core stream Mach number, P 0,e Representing the temperature of the wall at the inlet of the nozzle, n 1 、c 2 、n 3 Determining the parameter E to be estimated at the nozzle inlet as a coefficient to completely determine the Mach number M of the nozzle inlet in And total pressure P 0 H is half of the height y of the inlets of the spray pipes along with the distribution form of the height y of the inlets of the spray pipes.
Further, the fluid calculation software is CFX or Ansys Fluent.
Further, the step S7 specifically includes the steps of:
s71, determining Kalman gain by adopting an ensemble Kalman filtering method:
wherein
Is a matrix X of state vectors f Relative to the sample mean
R is a covariance matrix of wall pressure measurements;
s72, according to
And correcting the initial parameter to be estimated of the nozzle inlet, wherein the superscript a represents the corrected parameter.
The invention also provides a nozzle inlet non-uniform flow parameter reconstruction device, which comprises:
a calculation grid division module for writing the flow field parameter on each grid point as xi i ＝(ρ i ,u i ,p i ) Where the index i denotes a certain grid point, ρ i Denotes the density, u, of grid points i i Representing the x-direction velocity component, p, at a certain grid point i i Representing the pressure at grid point i;
spray pipe wall pressure measuring moduleThe method is used for measuring and obtaining the wall pressure of the spray pipe, and a vector Y ═ p is formed according to the wall pressure data of the spray pipe 1 p 2 p 3 … p l ) T Wherein the subscript l represents the number of pressure measurement points, and T represents the matrix transposition;
the observation matrix determining module is used for determining an observation matrix H according to the wall pressure measuring point position of the spray pipe in the test and the calculation grid;
the parameter to be estimated determining module is used for giving the distribution form of the Mach number and the pressure of the nozzle inlet according to a polynomial form and obtaining a parameter E to be estimated of the nozzle inlet according to the polynomial;
the initial sample set determining module is used for giving a sampling point number N, sampling in the initial estimation range of the parameter E to be estimated at the given nozzle inlet, and determining the initial sample set of the inlet parameters, wherein the combination of the parameters E to be estimated at different nozzle inlets corresponds to different inlet Mach numbers and pressure distribution forms;
a flow field parameter preliminary solving module for calling fluid calculation software to carry out the solution of the flow field of the spray pipe according to the combination of parameters E to be estimated of different spray pipe inlets in the initial sample set, obtaining the speed, density and pressure distribution of the flow field and obtaining a matrix X containing state vectors of all samples f ＝(x f(1) x f(2) … x f(N) ) Wherein:
xf＝(ξ 1 ,ξ 2 ,…,ξ i ,…,ξ m ,E) T for the state vector corresponding to the combination of the parameter E to be estimated at the inlet of each spray pipe, the subscript m represents the number of grid points, and the superscript f represents the state of the flow field obtained by calculating the flow field;
the parameter correction module is used for correcting the initial parameter to be estimated of the nozzle inlet;
and the flow field parameter iterative calculation module is used for generating a spray pipe inlet Mach number and a pressure profile based on the corrected spray pipe inlet to-be-estimated parameter, and iterating again until the difference between the spray pipe inlet to-be-estimated parameter and the last iteration step is smaller than a set threshold value, and calculating to obtain a spray pipe flow field parameter corresponding to the spray pipe wall surface pressure according to the converged spray pipe inlet to-be-estimated parameter.
In another aspect, the present invention further provides a storage medium, where the storage medium includes a stored program, and when the program runs, the apparatus on which the storage medium is located is controlled to execute the nozzle inlet non-uniform flow parameter reconstruction method.
The invention also provides electronic equipment comprising a memory, a processor and a computer program which is stored on the memory and can run on the processor, wherein the processor executes the program to realize the nozzle inlet non-uniform flow parameter reconstruction method.
The invention has the following beneficial effects:
according to the method for reconstructing the non-uniform flow parameters of the nozzle inlet, the polynomial form of the parameter distribution of the nozzle inlet is assumed, the flow field reconstruction of the nozzle is carried out based on the wall pressure data, the mach number and the pressure reconstruction precision of the nozzle inlet can be effectively improved (compared with the uniform inlet parameter assumption), and the matching degree of the nozzle profile and the inlet parameters in the nozzle design is improved; by calling fluid calculation software to carry out flow field calculation, experimental measurement data and a computational fluid mechanics method can be fully combined, and high-precision inlet parameter distribution and nozzle flow field reconstruction are achieved.
In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view of a hypersonic aircraft and nozzle.
FIG. 2 is a flow chart of a nozzle inlet non-uniform flow parameter reconstruction method according to a preferred embodiment of the invention.
FIG. 3 is a schematic flow chart illustrating a process for modifying an initial parameter to be estimated at a nozzle inlet.
FIG. 4 is a schematic block diagram of a nozzle inlet non-uniform flow parameter reconstruction device in accordance with a preferred embodiment of the present invention.
Fig. 5 is a schematic diagram of an electronic device in accordance with a preferred embodiment of the present invention.
In the figure: 1. an aircraft; 2. a nozzle; 3. a nozzle inlet; 4. a combustion chamber.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 2, a nozzle inlet non-uniform flow parameter reconstruction method includes the steps of:
s1, dividing calculation grids aiming at the jet pipe, and writing the flow field parameter on each grid point as xi i ＝(ρ i ,u i ,p i ) Where the subscript i denotes a certain grid point, ρ i Denotes the density, u, of grid points i i Representing the x-direction velocity component, p, at a certain grid point i i Representing the pressure at grid point i;
s2, measuring and obtaining the pressure of the wall surface of the spray pipe, and forming a vector Y (p) according to the pressure data of the wall surface of the spray pipe 1 p 2 p 3 … p l ) T Wherein the subscript l represents the number of pressure measurement points, and T represents the matrix transposition;
s3, determining an observation matrix H according to the wall pressure measuring point position of the spray pipe in the test and the calculation grid;
s4, giving the distribution form of the Mach number and the pressure of the nozzle inlet according to a polynomial form, and obtaining a parameter E to be estimated of the nozzle inlet according to the polynomial;
s5, setting the number N of sampling points, sampling in the initial estimation range of the parameter E to be estimated at the inlet of the given spray pipe, determining the initial sample set of the inlet parameter, wherein the combination of the parameters E to be estimated at the inlet of different spray pipes corresponds to different inlet Mach numbers and pressure distribution forms;
s6, according to different combinations of parameters E to be estimated of the nozzle inlets in the initial sample set, calling fluid computing software CFX or Ansys Fluent to carry out nozzle flow field solving, and obtaining the speed, density and sum of flow fieldsPressure distribution and obtaining a matrix X containing state vectors of all samples f ＝(x f(1) x f(2) … x f(N) ) Wherein:
x f ＝(ξ 1 ,ξ 2 ,…,ξ i ,…,ξ m ,E) T for a state vector corresponding to the combination of the parameter E to be estimated at the inlet of each spray pipe, the subscript m represents the number of grid points, and the superscript f represents the state of a flow field obtained by calculating the flow field;
s7, correcting the initial parameter to be estimated of the nozzle inlet;
and S8, generating a nozzle inlet Mach number and a pressure profile based on the corrected nozzle inlet parameter to be estimated, iterating again, and repeating the steps S6-S7 until the difference between the nozzle inlet parameter to be estimated and the last iteration step is smaller than a set threshold value, and calculating to obtain a nozzle flow field parameter corresponding to the nozzle wall surface pressure according to the converged nozzle inlet parameter to be estimated.
According to the method for reconstructing the non-uniform flow parameters of the nozzle inlet, the nozzle flow field reconstruction is carried out on the basis of wall pressure data and an iterative convergence mode by assuming a polynomial form of the parameter distribution of the nozzle inlet, so that the Mach number and the pressure reconstruction precision of the nozzle inlet can be effectively improved (compared with a uniform inlet parameter assumption), and the matching degree of the nozzle profile and the inlet parameters in the nozzle design is improved; by calling fluid calculation software to carry out flow field calculation, experimental measurement data and a computational fluid mechanics method can be fully combined, and high-precision inlet parameter distribution and nozzle flow field reconstruction are realized; in the embodiment, the non-uniform Mach number M of the nozzle inlet is obtained by reversely reconstructing the pressure distribution data of the nozzle measured through experiments in And total pressure P 0 The distribution of the pressure and the mach number of the inlet of the jet pipe is calculated by one-dimensional engineering, the problems that the distribution of the mach number and the pressure at the inlet of the jet pipe cannot be provided and the optimal design of the profile of the jet pipe is seriously influenced are solved, the distribution of the pressure and the mach number at the inlet of the jet pipe is significant for improving the performance of an aircraft, and the optimal design of the profile of the jet pipe is ensured.
In a preferred embodiment of the present invention, in step S3, when the observation matrix H is determined according to the wall pressure measurement point position of the nozzle wall and the calculation grid in the test, the element value of the observation matrix H corresponding to the position where the wall pressure measurement point position coincides with the calculation grid point or the distance is smaller than the set threshold is 1, otherwise, the element value of the observation matrix H is 0. The nozzle wall surface pressure measurement point of this embodiment is a sampling point on the computational grid through the observation matrix H, the value of each element in the observation matrix H is 1 or 0, the corresponding position where the measurement data can be obtained is 1, and the remaining positions are 0.
In a preferred embodiment of the present invention, the distribution form of the mach number and the pressure at the nozzle inlet given in the form of a polynomial is specifically:
the parameter E to be estimated at the nozzle inlet comprises M e 、n 1 、P 0,e 、c 2 And n 3 Wherein M is e Representing the nozzle inlet core stream Mach number, P 0,e Representing the temperature of the wall at the inlet of the nozzle, n 1 、c 2 、n 3 As a coefficient, the Mach number M of the nozzle inlet can be completely determined by determining the parameter E to be estimated of the nozzle inlet in And total pressure P 0 H is half of the height y of the inlet of the spray pipe along with the distribution form of the height y of the inlet of the spray pipe;
in this embodiment, the parameter to be estimated of the nozzle inlet is obtained by giving the mach number and the pressure distribution form of the nozzle inlet according to the polynomial form, and the purpose is to completely determine the mach number M of the nozzle inlet in And total pressure P 0 With the distribution form of the height y of the inlet of the spray pipe, a foundation is laid for the determination of the inlet parameters of the subsequent spray pipe.
As shown in fig. 3, in a preferred embodiment of the present invention, the step S7 specifically includes the steps of:
s71, determining Kalman gain by adopting an ensemble Kalman filtering method:
wherein
Is a matrix X of state vectors f Relative to the sample mean
R is a covariance matrix of wall pressure measurements;
s72, according to
And correcting the initial parameter to be estimated of the nozzle inlet, wherein the superscript a represents the corrected parameter.
In the embodiment, the Kalman gain is determined by adopting an ensemble Kalman filtering method, and meanwhile, the parameter to be estimated at the inlet of the spray pipe is corrected based on the Kalman gain, so that the accuracy of the parameter to be estimated at the inlet of the spray pipe is higher, and the result reliability is higher.
As shown in fig. 4, a preferred embodiment of the present invention further provides a nozzle inlet non-uniform flow parameter reconstruction device, comprising:
a calculation grid division module for writing the flow field parameter on each grid point as xi i ＝(ρ i ,u i ,p i ) Where the subscript i denotes a certain grid point, ρ i Denotes the density, u, of grid points i i Representing the x-direction velocity component, p, at a certain grid point i i Represents the pressure at grid point i;
the spray pipe wall surface pressure measuring module is used for measuring and obtaining spray pipe wall surface pressure, and forming a vector Y (p) according to spray pipe wall surface pressure data 1 p 2 p 3 … p l ) T Wherein the subscript l represents the number of pressure measurement points, and T represents the matrix transposition;
the observation matrix determining module is used for determining an observation matrix H according to the wall pressure measuring point position of the spray pipe in the test and the calculation grid;
the parameter to be estimated determining module is used for giving the distribution form of the Mach number and the pressure of the nozzle inlet according to a polynomial form and obtaining a parameter E to be estimated of the nozzle inlet according to the polynomial;
the initial sample set determining module is used for giving a sampling point number N, sampling in the initial estimation range of the parameter E to be estimated at the given nozzle inlet, and determining the initial sample set of the inlet parameters, wherein the combination of the parameters E to be estimated at different nozzle inlets corresponds to different inlet Mach numbers and pressure distribution forms;
a flow field parameter preliminary solving module for calling fluid calculation software to carry out the solution of the flow field of the spray pipe according to the combination of parameters E to be estimated of different spray pipe inlets in the initial sample set, obtaining the speed, density and pressure distribution of the flow field and obtaining a matrix X containing state vectors of all samples f ＝(x f(1) x f(2) … x f(N) ) Wherein:
x f ＝(ξ 1 ,ξ 2 ,…,ξ i ,…,ξ m ,E) T for the state vector corresponding to the combination of the parameter E to be estimated at the inlet of each spray pipe, the subscript m represents the number of grid points, and the superscript f represents the state of the flow field obtained by calculating the flow field;
the parameter correction module is used for correcting the initial parameter to be estimated of the nozzle inlet;
and the flow field parameter iteration calculation module is used for generating a spray pipe inlet Mach number and a pressure profile based on the corrected spray pipe inlet to-be-estimated parameter, and iterating again until the difference between the spray pipe inlet to-be-estimated parameter and the last iteration step is smaller than a set threshold value, and calculating according to the converged spray pipe inlet to-be-estimated parameter to obtain a spray pipe flow field parameter corresponding to the spray pipe wall pressure.
The nozzle inlet non-uniform flow parameter reconstruction device of the embodiment can perform nozzle flow field reconstruction based on wall pressure data and an iterative convergence mode by assuming a polynomial form of nozzle inlet parameter distribution, can effectively improve nozzle inlet Mach number and pressure reconstruction accuracy (compared with a uniform inlet parameter assumption), and is beneficial to improving the matching degree of a nozzle profile and inlet parameters in nozzle design; the flow field calculation is carried out by calling fluid calculation software, and experimental measurement data and a meter can be fully combinedThe computational fluid mechanics method realizes high-precision inlet parameter distribution and nozzle flow field reconstruction; in the embodiment, the non-uniform Mach number M of the nozzle inlet is obtained by reversely reconstructing the pressure distribution data of the nozzle measured through experiments in And total pressure P 0 The distribution of the pressure and the mach number of the inlet of the jet pipe is calculated by one-dimensional engineering, the problems that the distribution of the mach number and the pressure at the inlet of the jet pipe cannot be provided and the optimal design of the profile of the jet pipe is seriously influenced are solved, the distribution of the pressure and the mach number at the inlet of the jet pipe is significant for improving the performance of an aircraft, and the optimal design of the profile of the jet pipe is ensured.
In particular, the preferred embodiment of the present invention further provides a storage medium, which includes a stored program, and when the program runs, the storage medium controls a device in which the storage medium is located to execute the nozzle inlet non-uniform flow parameter reconstruction method.
As shown in fig. 5, in a preferred embodiment of the present invention, there is also provided an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the nozzle inlet non-uniform flow parameter reconstruction method when executing the computer program.
It should be noted that the steps illustrated in the flowcharts of the figures may be performed in a computer system such as a set of computer-executable instructions and that, although a logical order is illustrated in the flowcharts, in some cases, the steps illustrated or described may be performed in an order different than presented herein.
The functions of the method of the present embodiment, if implemented in the form of software functional units and sold or used as independent products, may be stored in one or more storage media readable by a computing device. Based on such understanding, part of the contribution of the embodiments of the present invention to the prior art or part of the technical solution may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computing device (which may be a personal computer, a server, a mobile computing device, a network device, or the like) to execute all or part of the steps of the method described in the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk, an optical disk, or other various media capable of storing program codes.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A nozzle inlet non-uniform flow parameter reconstruction method is characterized by comprising the following steps:
s1, dividing calculation grids aiming at the jet pipe, and writing the flow field parameter on each grid point as xi i ＝(ρ i ,u i ,p i ) Where the subscript i denotes a certain grid point, ρ i Denotes the density, u, of grid points i i Representing the x-direction velocity component, p, at a certain grid point i i Representing the pressure at grid point i;
s2, measuring and obtaining the wall pressure of the spray pipe, and forming a vector Y (p) according to the wall pressure data of the spray pipe 1 p 2 p 3 … p l ) T Wherein the subscript l represents the number of pressure measurement points, and T represents the matrix transposition;
s3, determining an observation matrix H according to the wall pressure measuring point position of the spray pipe in the test and the calculation grid;
s4, giving the distribution form of the Mach number and the pressure of the nozzle inlet according to a polynomial form, and obtaining a parameter E to be estimated of the nozzle inlet according to the polynomial;
s5, setting the number N of sampling points, sampling in the initial estimation range of the parameter E to be estimated at the inlet of the given spray pipe, determining the initial sample set of the inlet parameter, wherein the combination of the parameters E to be estimated at the inlet of different spray pipes corresponds to different inlet Mach numbers and pressure distribution forms;
s6, according to different combinations of parameters E to be estimated of the nozzle inlets in the initial sample set, calling fluid calculation software to carry out nozzle flow field calculationSolving to obtain the velocity, density and pressure distribution of the flow field and obtain a matrix X containing state vectors of all samples f ＝(x f(1) x f(2) … x f(N) ) Wherein:
x f ＝(ξ 1 ,ξ 2 ,…,ξ i ,…,ξ m ,E) T for the state vector corresponding to the combination of the parameter E to be estimated at the inlet of each spray pipe, the subscript m represents the number of grid points, and the superscript f represents the state of the flow field obtained by calculating the flow field;
s7, correcting the initial parameter to be estimated of the nozzle inlet;
and S8, generating a nozzle inlet Mach number and a pressure profile based on the corrected nozzle inlet parameter to be estimated, iterating again, and repeating the steps S6-S7 until the difference between the nozzle inlet parameter to be estimated and the last iteration step is smaller than a set threshold value, and calculating to obtain a nozzle flow field parameter corresponding to the nozzle wall surface pressure according to the converged nozzle inlet parameter to be estimated.
2. The nozzle inlet non-uniform flow parameter reconstruction method according to claim 1, wherein in step S3, when the observation matrix H is determined according to the nozzle wall pressure measurement point position and the calculation grid in the test, the element value of the observation matrix H corresponding to the position where the wall pressure measurement point position coincides with the calculation grid point or the distance between the wall pressure measurement point position and the calculation grid point is smaller than the set threshold value is 1, otherwise, the element value of the observation matrix H is 0.
3. The nozzle inlet non-uniform flow parameter reconstruction method according to claim 1, wherein the distribution form of the mach number and the pressure of the nozzle inlet given according to the polynomial form is specifically as follows:
the parameter E to be estimated at the nozzle inlet comprises M e 、n 1 、P 0,e 、c 2 And n 3 Wherein, M is e Showing central flow of nozzle inletHertz number, P 0,e Representing the temperature of the wall at the inlet of the nozzle, n 1 、c 2 、n 3 Determining the parameter E to be estimated of the nozzle inlet as a coefficient to completely determine the Mach number M of the nozzle inlet in And total pressure P 0 H is half of the height y of the inlets of the spray pipes along with the distribution form of the height y of the inlets of the spray pipes.
4. The nozzle inlet non-uniform flow parameter reconstruction method of claim 1,
the fluid calculation software is CFX or Ansys Fluent.
5. The nozzle inlet non-uniform flow parameter reconstruction method according to claim 1, wherein the step S7 specifically comprises the steps of:
s71, determining Kalman gain by adopting an ensemble Kalman filtering method:
wherein
Is a matrix X of state vectors f Relative to the sample mean
R is a covariance matrix of wall pressure measurements;
s72, according to
And correcting the initial parameter to be estimated of the nozzle inlet, wherein the superscript a represents the corrected parameter.
6. A nozzle inlet non-uniform flow parameter reconstruction device, comprising:
a computational meshing module for meshing each meshThe flow field parameter on the grid point is written as xi i ＝(ρ i ,u i ,p i ) Where the subscript i denotes a certain grid point, ρ i Denotes the density, u, of grid points i i Representing the x-direction velocity component, p, at a certain grid point i i Representing the pressure at grid point i;
the spray pipe wall surface pressure measuring module is used for measuring and obtaining spray pipe wall surface pressure, and forming a vector Y (p) according to spray pipe wall surface pressure data 1 p 2 p 3 … p l ) T Wherein, subscript l represents the number of pressure measurement points, and T represents the matrix transposition;
the observation matrix determining module is used for determining an observation matrix H according to the wall pressure measuring point position of the spray pipe in the test and the calculation grid;
the to-be-estimated parameter determining module is used for giving the distribution form of the Mach number and the pressure of the nozzle inlet according to a polynomial form and obtaining a to-be-estimated parameter E of the nozzle inlet according to the polynomial;
the initial sample set determining module is used for giving a sampling point number N, sampling in the initial estimation range of the parameter E to be estimated at the given nozzle inlet, and determining the initial sample set of the inlet parameters, wherein the combination of the parameters E to be estimated at different nozzle inlets corresponds to different inlet Mach numbers and pressure distribution forms;
a flow field parameter preliminary solving module for calling fluid calculation software to carry out the solution of the flow field of the spray pipe according to the combination of parameters E to be estimated of different spray pipe inlets in the initial sample set, obtaining the speed, density and pressure distribution of the flow field and obtaining a matrix X containing state vectors of all samples f ＝(x f(1) x f(2) … x f(N) ) Wherein:
x f ＝(ξ 1 ,ξ 2 ,…,ξ i ,…,ξ m ,E) T for the state vector corresponding to the combination of the parameter E to be estimated at the inlet of each spray pipe, the subscript m represents the number of grid points, and the superscript f represents the state of the flow field obtained by calculating the flow field;
the parameter correction module is used for correcting the initial parameter to be estimated of the nozzle inlet;
and the flow field parameter iterative calculation module is used for generating a spray pipe inlet Mach number and a pressure profile based on the corrected spray pipe inlet to-be-estimated parameter, and iterating again until the difference between the spray pipe inlet to-be-estimated parameter and the last iteration step is smaller than a set threshold value, and calculating to obtain a spray pipe flow field parameter corresponding to the spray pipe wall surface pressure according to the converged spray pipe inlet to-be-estimated parameter.
7. A storage medium comprising a stored program, wherein the program, when executed, controls a device in which the storage medium is located to perform a nozzle inlet non-uniform flow parameter reconstruction method as claimed in any one of claims 1 to 5.
8. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor, when executing the program, implements the nozzle inlet non-uniform flow parameter reconstruction method of any of claims 1-5.
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