CN112069597B - Supersonic velocity spray pipe flow field and inlet parameter reconstruction method, device, medium and equipment - Google Patents

Supersonic velocity spray pipe flow field and inlet parameter reconstruction method, device, medium and equipment Download PDF

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CN112069597B
CN112069597B CN202010867643.1A CN202010867643A CN112069597B CN 112069597 B CN112069597 B CN 112069597B CN 202010867643 A CN202010867643 A CN 202010867643A CN 112069597 B CN112069597 B CN 112069597B
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nozzle
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王前程
赵玉新
赵一龙
王成龙
杨润泽
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Abstract

The invention discloses a method, a device, a medium and equipment for reconstructing a flow field and inlet parameters of a supersonic velocity spray pipe, wherein the method comprises the following steps: s1, dividing calculation grids aiming at the spray pipe, and enabling the spray pipe inlet parameters and flow field parameters on all grid points of the spray pipe to form state vectors; 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, sampling in the initial estimation range of the given nozzle inlet parameter according to the given sampling point number N, and determining an initial sample set; s5, obtaining a matrix of flow field parameters and state vectors of the initial spray pipes based on a reverse characteristic line method according to different spray pipe parameter combinations in the initial sample set; s6, correcting the parameters of the nozzle inlet; and S7, iterating to converge based on the corrected nozzle inlet parameters, and calculating to obtain nozzle flow field parameters corresponding to the nozzle wall surface pressure. The invention can realize the accurate and fast reconstruction of the inlet parameters of the spray pipe.

Description

Supersonic velocity spray pipe flow field and inlet parameter reconstruction method, device, medium and equipment
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 a supersonic velocity spray pipe flow field and inlet parameters.
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. The accurate determination of the parameters of the nozzle inlet is of great significance for improving the performance of the hypersonic aircraft.
Because the inlet temperature of the scramjet engine spray pipe is high, the speed is high, the direct measurement difficulty of inlet parameters is high, the existing inlet parameter determination mainly depends on rough thermodynamic estimation, the accuracy of the inlet parameter determination is low, the matching of the spray pipe molded surface and the outlet parameters of the combustion chamber 4 is seriously influenced, and the thrust loss of the spray pipe is large.
The main problems of the existing method for determining the parameters of the nozzle inlet comprise that: the estimation precision of the parameters of the inlet of the spray pipe is low, the effect is poor, the error range cannot be given, and the optimal design of the molded surface of the spray pipe is seriously influenced.
Disclosure of Invention
The invention provides a supersonic velocity spray pipe flow field and inlet parameter reconstruction method, and aims to solve the technical problems that the existing spray pipe inlet parameter determination method is low in spray pipe inlet parameter estimation precision, poor in effect and incapable of providing an error range.
The technical scheme adopted by the invention is as follows:
a supersonic velocity spray pipe flow field and inlet parameter reconstruction method comprises the following steps:
s1, aiming at the nozzle, dividing and calculating the grid, and dividing the Mach number M of the nozzle inlet in Pressure p in Specific heat ratio gamma and flow field parameter xi on all grid points of spray pipe i ＝(ρ i ,u i ,p i ) Form a state vector x f ＝(ξ 1 ,ξ 2 ,…,ξ m ,γ,M in ,p in ) T Where i represents a certain grid point, m represents the number of grid points, T represents matrix transposition, f represents a flow field state obtained by calculating a flow field, 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 l represents the number of pressure measurements;
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, setting the number of sampling points N and the Mach number M at the inlet of the given spray pipe in Pressure p in Sampling the initial estimation range of the specific heat ratio gamma, and determining an initial sample set of the inlet parameters of the spray pipe;
s5, according to different nozzle inlet Mach numbers M in the initial sample set in Pressure p in And the specific heat ratio gamma is combined, the flow field parameters of the spray pipe are solved based on a reverse characteristic line method, the flow field parameters of the initial spray pipe are obtained, the flow field parameters of the initial spray pipe comprise speed, density and pressure, and a matrix X containing state vectors of all samples is obtained f ＝(x f(1) x f(2) … x f (N) )；
S6 Mach number M of inlet of counter nozzle in Pressure p in Correcting the specific heat ratio gamma;
s7, iterating again based on the corrected nozzle inlet Mach number and pressure, and repeating the steps S5-S6 until the nozzle inlet Mach number M in Pressure p in And when the difference between the specific heat ratio gamma and the last iteration step is less than a set threshold value, the Mach number M of the spray pipe inlet according to convergence in Pressure p in And calculating the specific heat ratio gamma to obtain the flow field parameters of the spray pipe corresponding to the wall pressure of the spray pipe.
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, in step S5, the solving of the nozzle flow field parameter based on the inverse characteristic line method specifically includes the steps of:
based on the divided calculation grids and the given inlet parameters, the flow field is solved by utilizing the reverse characteristic lines and grid layer by grid layer along the flow direction, so that the flow field parameters of the whole spray pipe are solved.
Further, the method for solving the flow field parameters of the whole spray pipe by solving the flow field layer by layer along the flow direction by using a reverse characteristic line based on the divided calculation grids and the given inlet parameters specifically comprises the following steps:
s51, solving flow field parameters of all points to be solved on the first grid layer to be solved in the flow direction by using the reverse characteristic line;
and S52, repeating the step S51, and solving the flow field parameters by grid layers along the flow direction to realize the solution of the flow field parameters of the whole spray pipe.
Further, the step S51 specifically includes:
s511, determining the coordinate of the point j to be solved on the (n + 1) th grid layer as (x) j ,y j ) Two inverse characteristic lines C-and C emanating from point j + The intersection points with the adjacent nth grid layer are respectively e and h, and subscripts "-" and "+" respectively represent a right-row reverse characteristic line and a left-row reverse characteristic line;
s512, finding three points which are a, b and c respectively at the position on the nth grid layer and closest to the point j;
s513, the estimates of the velocity of point e and h are given by linear interpolation:
Figure BDA0002650191290000031
Figure BDA0002650191290000032
wherein the superscript "0" represents the initial estimate, v represents the y-direction velocity component, and u represents the x-direction velocity component;
s514, obtaining a reverse characteristic line C - And C + Slope of (c):
λ + ＝tan(θ + +α + )
λ - ＝tan(θ - -α - )
wherein,
Figure BDA0002650191290000041
Figure BDA0002650191290000042
Figure BDA0002650191290000043
Figure BDA0002650191290000044
in the above-mentioned relation, the first and second,
Figure BDA0002650191290000045
in absolute value of velocity, α is Mach angle, θ is flow angle, a is speed of sound, T 0 R is the gas constant for the total temperature;
s515, according to the coordinate (x) of the point j j ,y j ) And reverse characteristic line C - 、C + Slope of (a) < lambda > - 、λ + Calculating to obtain two reverse characteristic lines C - 、C + The coordinates of the intersection points e and h with the n-th mesh layer are (x), respectively e ,y e ) And (x) h ,y h )；
S516, updating the speeds of the points e and h by linear interpolation according to the coordinates of the points e and h and the speed values of two adjacent points on the nth grid layer
Figure BDA0002650191290000046
And
Figure BDA0002650191290000047
the superscript "1" indicates the updated value;
s517, according to the updated speed of the points e and h, repeating the steps S514 to S516 until the coordinates (x) of the points e and h e ,y e ) And (x) h ,y h ) Has little difference with the previous iteration stepSetting a threshold value;
s518 coordinates (x) according to points e and h e ,y e ) And (x) h ,y h ) And corresponding speed, calculating the speed of the obtained point j by adopting a forward characteristic line method:
A + (u 4 -u 2 )+B + (v 4 -v 2 )-S + (x 4 -x 2 )＝0
A - (u 4 -u 1 )+B - (v 4 -v 1 )-S - (x 4 -x 1 )＝0
wherein A, B, S is a coefficient, and the specific calculation method is as follows:
Figure BDA0002650191290000051
B + ＝(2u + v + -A + λ + ),B - ＝(2u - v - -A - λ - )
Figure BDA0002650191290000052
in the calculation of S, δ — 1 for an axisymmetric configuration; for a two-dimensional planar configuration, δ — 0;
s519, Mach number M of point j is obtained j ：
Figure BDA0002650191290000053
Wherein,
Figure BDA0002650191290000054
s5110 pressure p at point j j And temperature T j Based on total temperature T 0 And total pressure p 0 And calculating according to an isentropic relation to obtain:
Figure BDA0002650191290000055
Figure BDA0002650191290000056
s5111, calculating density rho of point j by using gas state equation j ：
Figure BDA0002650191290000057
And S5112, repeating the step S511 to the step S5111, and obtaining the flow field parameters of the rest points to be obtained on the (n + 1) th grid layer.
Further, the step S6 specifically includes the steps of:
s61, determining Kalman gain by adopting an ensemble Kalman filtering method:
Figure BDA0002650191290000058
wherein
Figure BDA0002650191290000059
Is a matrix X of state vectors f Relative to the sample mean
Figure BDA00026501912900000510
R is a covariance matrix of wall pressure measurements;
s62, according to
Figure BDA0002650191290000061
And (4) correcting the Mach number, the pressure and the specific heat ratio of the nozzle inlet, wherein a represents a corrected parameter.
The invention also provides a reverse rapid reconstruction device of the supersonic velocity spray pipe flow field and the inlet flow parameters thereof, which comprises:
computing networkA grid division module for dividing the calculation grid according to the spray pipe and dividing the Mach number M of the spray pipe inlet in Pressure p in Specific heat ratio gamma and flow field parameter xi on all grid points of spray pipe i ＝(ρ i ,u i ,p i ) Form a state vector x f ＝(ξ 1 ,ξ 2 ,…,ξ m ,γ,M in ,p in ) T Where i represents a certain grid point, m represents the number of grid points, T represents matrix transposition, f represents a flow field state obtained by calculating a flow field, 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 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 the spray pipe wall surface pressure data 1 p 2 p 3 … p l ) T Wherein l represents the number of pressure measurements;
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;
an initial sample set determining module for setting the number N of sampling points and the Mach number M at the inlet of the given nozzle in Pressure p in Sampling the initial estimation range of the specific heat ratio gamma, and determining an initial sample set of the inlet parameters of the spray pipe;
a flow field parameter preliminary solving module for solving the flow field parameter according to different nozzle inlet Mach numbers M in the initial sample set in Pressure p in And the specific heat ratio gamma is combined, the flow field parameters of the spray pipe are solved based on a reverse characteristic line method, the flow field parameters of the initial spray pipe are obtained, the flow field parameters of the initial spray pipe comprise speed, density and pressure, and a matrix X containing state vectors of all samples is obtained f ＝(x f(1) x f(2) … x f(N) )；
A parameter correction module for correcting the Mach number M of the nozzle inlet in Pressure p in Correcting the specific heat ratio gamma;
a flow field parameter iterative computation module for calculating the flow field parameter based on the corrected nozzle inletRepeating the iteration of Mach number and pressure until the Mach number M of the nozzle inlet in Pressure p in And when the difference between the specific heat ratio gamma and the last iteration step is less than a set threshold value, the Mach number M of the spray pipe inlet according to convergence in Pressure p in And calculating the specific heat ratio gamma to obtain a spray pipe flow field parameter corresponding to the wall pressure of the spray pipe.
The invention also provides a storage medium which comprises a stored program, and when the program runs, the device where the storage medium is located is controlled to execute the reconstruction method of the supersonic velocity nozzle flow field and the inlet parameter.
The invention also provides electronic equipment which comprises 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 reconstruction method of the flow field and the inlet parameters of the supersonic velocity nozzle.
The invention has the following beneficial effects:
the supersonic velocity spray pipe flow field and inlet parameter reconstruction method realizes reverse reconstruction of spray pipe inlet parameters based on experimental data based on measured wall surface pressure data by combining a reverse characteristic line method and an iterative convergence mode, has high accuracy and reliability of reconstruction results, and can realize reconstruction of the flow field parameters of the whole spray pipe; the flow field reconstruction by adopting the characteristic line method has short time consumption, high speed and high efficiency, and can realize quick reconstruction.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. 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 schematic flow chart of a supersonic velocity nozzle flow field and inlet parameter reconstruction method according to a preferred embodiment of the present invention;
FIG. 3 is a schematic flow chart of the preferred embodiment of the present invention for solving the parameters of the entire nozzle flow field by solving the flow field from grid layer to grid layer in the flow direction using inverse eigen lines based on the divided computational grids and the given inlet parameters;
FIG. 4 is a schematic diagram of a unit process for point solution in a flow field according to the present invention;
FIG. 5 is a schematic view of a flow field parameter specific process for determining all points to be determined on a first grid layer to be determined in a flow direction by using a reverse characteristic line according to the present invention;
FIG. 6 is a schematic view of the process for modifying the Mach number, pressure and specific heat ratio of the nozzle inlet according to the present invention;
FIG. 7 is a schematic view of a supersonic nozzle flow field and inlet parameter reconstruction device module according to a preferred embodiment of the present invention;
fig. 8 is a schematic diagram of an electronic device of a preferred embodiment of the 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 embodiments with reference to the attached drawings.
As shown in fig. 2, a method for reconstructing a flow field and inlet parameters of a supersonic nozzle includes the steps of:
s1, aiming at the nozzle, dividing a calculation grid and dividing the Mach number M of the nozzle inlet in Pressure p in Specific heat ratio gamma and flow field parameter xi on all grid points of spray pipe i ＝(ρ i ,u i ,p i ) Form a state vector x f ＝(ξ 1 ,ξ 2 ,…,ξ m ,γ,M in ,p in ) T Where i represents a certain grid point, m represents the number of grid points, T represents matrix transposition, f represents a flow field state obtained by calculating a flow field, 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 l represents the number of pressure measurements;
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, setting the number of sampling points N and the Mach number M at the inlet of the given nozzle in Pressure p in Sampling the initial estimation range of the specific heat ratio gamma, and determining an initial sample set of the inlet parameters of the spray pipe;
s5, according to different nozzle inlet Mach numbers M in the initial sample set in Pressure p in And the specific heat ratio gamma is combined, the flow field parameters of the spray pipe are solved based on a reverse characteristic line method, the flow field parameters of the initial spray pipe are obtained, the flow field parameters of the initial spray pipe comprise speed, density and pressure, and a matrix X containing state vectors of all samples is obtained f ＝(x f(1) x f(2) … x f (N) )；
S6 Mach number M of inlet of counter nozzle in Pressure p in Correcting the specific heat ratio gamma;
s7, iterating again based on the corrected nozzle inlet Mach number and pressure, and repeating the steps S5-S6 until the nozzle inlet Mach number M in Pressure p in When the difference between the specific heat ratio gamma and the last iteration step is smaller than a set threshold value, the Mach number M of the spray pipe inlet is determined according to the convergence in Pressure p in And calculating the specific heat ratio gamma to obtain the final spray pipe flow field parameter corresponding to the wall pressure of the spray pipe.
The supersonic velocity spray pipe flow field and inlet parameter reconstruction method of the embodiment is based on measured wall surface pressure data, realizes reverse reconstruction of spray pipe inlet parameters based on experimental data by combining a reverse characteristic line method and an iterative convergence mode, has high reconstruction result precision and reliability, and can realize accurate reconstruction of the whole spray pipe flow field parameters; the flow field reconstruction by adopting the characteristic line method has short time consumption, high speed and high efficiency, can realize quick reconstruction, overcomes the defects of low estimation precision, poor effect and incapability of giving an error range of the nozzle inlet parameter in the existing nozzle inlet parameter determination method, has important significance for improving the performance of the hypersonic aerocraft and ensures the optimal design of the nozzle profile.
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, in step S5, the solving of the nozzle flow field parameter based on the inverse characteristic line method specifically includes the steps of:
based on the divided calculation grids and the given inlet parameters, the flow field is solved by utilizing the reverse characteristic lines and grid layer by grid layer along the flow direction, so that the flow field parameters of the whole spray pipe are solved.
As shown in fig. 3, in a preferred embodiment of the present invention, the solving of the flow field parameters of the entire nozzle is implemented by solving the flow field layer by the grid layer in the flow direction by using the inverse characteristic line based on the divided computational grid and the given inlet parameters, and specifically includes the steps of:
s51, solving flow field parameters of all points to be solved on the first grid layer to be solved in the flow direction by using the reverse characteristic line;
and S52, solving the flow field parameters one by one in the flow direction to realize the solution of the flow field parameters of the whole spray pipe.
As shown in fig. 4, a unit process of solving the inner point of the flow field is shown, in the figure, the flow field parameter on the (n + 1) th grid layer is to be solved, the flow field parameter on the (n) th and (n-1) th grid layers is known, and the unit process of solving the inner point of the flow field by the inverse eigen-line method is described below by taking the solution of the j point on the (n + 1) th grid layer as an example.
As shown in fig. 5, in a preferred embodiment of the present invention, the step S51 specifically includes:
s511, determining the coordinate of the point j to be solved on the (n + 1) th grid layer as (x) j ,y j ) Two inverse characteristic lines C from point j - And C + The intersection points with the adjacent nth grid layer are respectively e and h, and subscripts "-" and "+" respectively represent a right-row reverse characteristic line and a left-row reverse characteristic line;
s512, finding three points which are a, b and c respectively at the position on the nth grid layer and closest to the point j;
s513, the estimates of the velocity of point e and h are given by linear interpolation:
Figure BDA0002650191290000101
Figure BDA0002650191290000102
wherein the superscript "0" represents the initial estimate, v represents the y-direction velocity component, and u represents the x-direction velocity component;
s514, obtaining a reverse characteristic line C - And C + Slope of (d):
λ + ＝tan(θ + +α + )
λ - ＝tan(θ - -α - )
wherein,
Figure BDA0002650191290000103
Figure BDA0002650191290000104
Figure BDA0002650191290000105
Figure BDA0002650191290000111
in the above-mentioned relation, the first and second,
Figure BDA0002650191290000112
in absolute value of velocity, α is Mach angle, θ is flow angle, a is speed of sound, T 0 R is the gas constant for the total temperature;
s515, according to the coordinate (x) of the point j j ,y j ) And reverse characteristic line C - 、C + Slope of (a) < lambda > - 、λ + Calculating to obtain two reverse characteristic lines C - 、C + The coordinates of the intersection points e and h with the nth mesh layer are (x), respectively e ,y e ) And (x) h ,y h )；
S516, updating the speeds of the points e and h by linear interpolation according to the coordinates of the points e and h and the speed values of two adjacent points on the nth grid layer
Figure BDA0002650191290000116
And
Figure BDA0002650191290000117
the superscript "1" represents the updated value;
s517, repeating the steps S514 to S516 according to the updated speed of the points e and h until the coordinates (x) of the points e and h e ,y e ) And (x) h ,y h ) The difference with the last iteration step is less than a set threshold value;
s518 coordinates (x) according to points e and h e ,y e ) And (x) h ,y h ) And corresponding speed, calculating the speed of the obtained point j by adopting a forward characteristic line method:
A + (u 4 -u 2 )+B + (v 4 -v 2 )-S + (x 4 -x 2 )＝0
A - (u 4 -u 1 )+B - (v 4 -v 1 )-S - (x 4 -x 1 )＝0
wherein A, B, S is a coefficient, and the specific calculation method is as follows:
Figure BDA0002650191290000113
B + ＝(2u + v + -A + λ + ),B - ＝(2u - v - -A - λ - )
Figure BDA0002650191290000114
in the calculation of S, δ — 1 for an axisymmetric configuration; for a two-dimensional planar configuration, δ — 0;
s519, Mach number M of point j is obtained j ：
Figure BDA0002650191290000115
Wherein,
Figure BDA0002650191290000121
s5110, pressure p of Point j j And temperature T j Based on total temperature T 0 And total pressure p 0 And calculating according to an isentropic relation to obtain:
Figure BDA0002650191290000122
Figure BDA0002650191290000123
s5111, calculating density rho of point j by using gas state equation j ：
Figure BDA0002650191290000124
And S5112, repeating the step S511 to the step S5111, and obtaining the flow field parameters of the rest points to be obtained on the (n + 1) th grid layer.
The flow field parameter reverse reconstruction based on experimental data is realized by a method of fusing reverse characteristic lines and an iterative convergence mode, the accuracy and reliability of the reconstruction result are high, and the accurate reconstruction of the flow field parameter of the whole spray pipe can be realized; the flow field reconstruction method adopting the characteristic line method has the advantages of short time consumption, high speed and high efficiency, can realize quick reconstruction, overcomes the defects of low estimation precision, poor effect and incapability of giving an error range of the jet pipe inlet parameter in the existing jet pipe inlet parameter determination method, and lays a foundation for determining the subsequent jet pipe inlet parameter by accurately determining the flow field parameter.
As shown in fig. 6, in a preferred embodiment of the present invention, the step S6 specifically includes the steps of:
s61, determining Kalman gain by adopting an ensemble Kalman filtering method:
Figure BDA0002650191290000125
wherein
Figure BDA0002650191290000126
Is a matrix X of state vectors f Relative to the sample mean
Figure BDA0002650191290000127
R is a covariance matrix of wall pressure measurements;
s62, according to
Figure BDA0002650191290000128
Mach number of inlet of counter nozzlePressure and specific heat ratio, and a represents a corrected parameter.
In the embodiment, the Kalman gain is determined by adopting an ensemble Kalman filtering method, and meanwhile, the Mach number, the pressure and the specific heat ratio of the inlet of the spray pipe are corrected based on the Kalman gain, so that the accuracy of the inlet of the spray pipe is higher, and the reliability of a result is high.
As shown in fig. 7, a preferred embodiment of the present invention further provides a device for rapidly reconstructing a supersonic nozzle flow field and an inlet flow parameter thereof in reverse direction, including:
a calculation grid division module for dividing calculation grids aiming at the spray pipe and dividing the Mach number M of the spray pipe inlet in Pressure p in Specific heat ratio gamma and flow field parameter xi on all grid points of spray pipe i ＝(ρ i ,u i ,p i ) Form a state vector x f ＝(ξ 1 ,ξ 2 ,…,ξ m ,γ,M in ,p in ) T Where i represents a certain grid point, m represents the number of grid points, T represents matrix transposition, f represents a flow field state obtained by calculating a flow field, ρ i Denotes the density, u, of grid points i i Representing the x-direction velocity component, p, of a certain grid point i i 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 l represents the number of pressure measurements;
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;
an initial sample set determining module for setting the number N of sampling points and the Mach number M at the inlet of the given nozzle in Pressure p in Sampling the initial estimation range of the specific heat ratio gamma, and determining an initial sample set of the parameters of the inlet of the spray pipe;
a flow field parameter preliminary solving module for solving the flow field parameter according to different nozzle inlet Mach numbers M in the initial sample set in Pressure p in Specific heat ratio gamma groupAnd solving the flow field parameters of the spray pipe based on a reverse characteristic line method to obtain the flow field parameters of the initial spray pipe, wherein the flow field parameters of the initial spray pipe comprise speed, density and pressure, and a matrix X containing state vectors of all samples is obtained f ＝(x f(1) x f(2) … x f(N) )；
A parameter correction module for correcting the Mach number M of the nozzle inlet in Pressure p in Correcting the specific heat ratio gamma;
the flow field parameter iterative computation module is used for iterating again based on the corrected nozzle inlet Mach number and pressure until the nozzle inlet Mach number M in Pressure p in And when the difference between the specific heat ratio gamma and the last iteration step is less than a set threshold value, the Mach number M of the spray pipe inlet according to convergence in Pressure p in And calculating the specific heat ratio gamma to obtain a spray pipe flow field parameter corresponding to the wall pressure of the spray pipe.
The supersonic velocity spray pipe flow field and the reverse rapid reconstruction device of the inlet flow parameters thereof in the embodiment realize the reverse reconstruction of the spray pipe inlet parameters based on experimental data based on the measured wall surface pressure data by combining a reverse characteristic line method and an iterative convergence mode, have high accuracy and reliability of the reconstruction result, and can realize the accurate reconstruction of the flow field parameters of the whole spray pipe; the flow field reconstruction by adopting the characteristic line method is short in time consumption, high in speed and high in efficiency, can realize rapid reconstruction, overcomes the defects that the existing method for determining the parameters of the nozzle inlet is low in estimation precision, poor in effect and incapable of providing an error range, has important significance for improving the performance of the hypersonic aerocraft and ensures the optimal design of the molded surface of the nozzle.
Specifically, in a preferred embodiment of the present invention, a storage medium is further provided, 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 supersonic nozzle flow field and inlet parameter reconstruction method.
As shown in fig. 8, in a preferred embodiment of the present invention, there is further provided an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, and when the processor executes the computer program, the processor implements the supersonic nozzle flow field and inlet parameter reconstruction method.
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 or an optical disk, and 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 (9)

1. A supersonic velocity spray pipe flow field and inlet parameter reconstruction method is characterized by comprising the following steps:
s1, aiming at the nozzle, dividing a calculation grid and dividing the Mach number M of the nozzle inlet in Pressure p in Specific heat ratio gamma and flow field parameter xi on all grid points of spray pipe i ＝(ρ i ,u i ,p i ) Form a state vector x f ＝(ξ 1 ,ξ 2 ,…,ξ m ,γ,M in ,p in ) T Wherein i represents a certain grid point, m represents the number of grid points, T represents a matrix transposition, f represents a flow field state obtained by calculating a flow field, ρ i Density, u, representing grid points i i Representing the x-direction velocity component, p, of 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 l represents the number of pressure points;
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, setting the number of sampling points N and the Mach number M at the inlet of the given spray pipe in Pressure p in Sampling the initial estimation range of the specific heat ratio gamma, and determining an initial sample set of the parameters of the inlet of the spray pipe;
s5, according to different nozzle inlet Mach numbers M in the initial sample set in Pressure p in And the specific heat ratio gamma is combined, the flow field parameters of the spray pipe are solved based on a reverse characteristic line method, the flow field parameters of the initial spray pipe are obtained, the flow field parameters of the initial spray pipe comprise speed, density and pressure, and a matrix X containing state vectors of all samples is obtained f ＝(x f(1) x f(2) … x f(N) )；
S6 Mach number M of inlet of counter nozzle in Pressure p in Correcting the specific heat ratio gamma;
s7, iterating again based on the corrected nozzle inlet Mach number and pressure, and repeating the steps S5-S6 until the nozzle inlet Mach number M in Pressure p in And when the difference between the specific heat ratio gamma and the last iteration step is less than a set threshold value, the Mach number M of the spray pipe inlet according to convergence in Pressure p in And calculating the specific heat ratio gamma to obtain the final spray pipe flow field parameter corresponding to the wall pressure of the spray pipe.
2. The method for reconstructing the flow field and inlet parameters of the supersonic nozzle according to claim 1, wherein in step S3, when the observation matrix H is determined according to the wall pressure measuring point position of the nozzle in the test and the calculation grid, the element value of the observation matrix H corresponding to the position where the wall pressure measuring point position coincides with the calculation grid point or the distance between the wall pressure measuring point position and the calculation grid point is smaller than the set threshold is 1, otherwise, the element value of the observation matrix H is 0.
3. The supersonic velocity nozzle flow field and inlet parameter reconstruction method according to claim 1, wherein in step S5, the nozzle flow field parameter solution based on the inverse eigen-curve method specifically includes the steps of:
based on the divided calculation grids and the given inlet parameters, the flow field is solved by utilizing the reverse characteristic lines through grid layers along the flow direction, so that the flow field parameters of the whole spray pipe are solved.
4. The supersonic velocity nozzle flow field and inlet parameter reconstruction method according to claim 3, wherein the solving of the flow field parameters of the entire nozzle is realized by solving the flow field layer by layer along the flow direction by using a reverse characteristic line based on the divided calculation grid and the given inlet parameters, specifically comprising the steps of:
s51, solving flow field parameters of all points to be solved on the first grid layer to be solved in the flow direction by using the reverse characteristic line;
and S52, solving the flow field parameters one by one in the flow direction to realize the solution of the flow field parameters of the whole spray pipe.
5. The supersonic nozzle flow field and inlet parameter reconstruction method according to claim 4, wherein the step S51 specifically comprises:
s511, determining the coordinate of the point j to be solved on the (n + 1) th grid layer as (x) j ,y j ) Two inverse characteristic lines C emanating from point j - And C + The intersections with the adjacent nth grid layer are e and h, respectively, and the subscripts "-" and "+" represent the right and left rows of reverse feature lines, respectivelyA reverse characteristic line is formed;
s512, finding three points which are a, b and c respectively at the position on the nth grid layer and closest to the point j;
s513, the estimates of the velocity of point e and h are given by linear interpolation:
Figure FDA0002650191280000031
Figure FDA0002650191280000032
wherein the superscript "0" represents the initial estimate, v represents the y-direction velocity component, and u represents the x-direction velocity component;
s514, obtaining a reverse characteristic line C - And C + Slope of (d):
λ + ＝tan(θ + +α + )
λ - ＝tan(θ - -α - )
wherein,
Figure FDA0002650191280000033
Figure FDA0002650191280000034
Figure FDA0002650191280000035
Figure FDA0002650191280000036
in the above-mentioned relation, the first and second,
Figure FDA0002650191280000037
in absolute value of velocity, α is Mach angle, θ is flow angle, a is speed of sound, T 0 R is the gas constant for the total temperature;
s515, according to the coordinate (x) of the point j j ,y j ) And reverse characteristic line C - 、C + Slope of (a) < lambda > - 、λ + Calculating to obtain two reverse characteristic lines C - 、C + The coordinates of the intersection points e and h with the nth mesh layer are (x), respectively e ,y e ) And (x) h ,y h )；
S516, updating the speeds of the points e and h by linear interpolation according to the coordinates of the points e and h and the speed values of two adjacent points on the nth grid layer
Figure FDA0002650191280000038
And
Figure FDA0002650191280000039
the superscript "1" represents the updated value;
s517, according to the updated speed of the points e and h, repeating the steps S514 to S516 until the coordinates (x) of the points e and h e ,y e ) And (x) h ,y h ) The difference with the last iteration step is smaller than a set threshold value;
s518 coordinates (x) according to points e and h e ,y e ) And (x) h ,y h ) And corresponding speed, calculating the speed of the obtained point j by adopting a forward characteristic line method:
A + (u 4 -u 2 )+B + (v 4 -v 2 )-S + (x 4 -x 2 )＝0
A - (u 4 -u 1 )+B - (v 4 -v 1 )-S - (x 4 -x 1 )＝0
wherein A, B, S is a coefficient, and the specific calculation mode is as follows:
Figure FDA0002650191280000041
B + ＝(2u + v + -A + λ + ),B - ＝(2u - v - -A - λ - )
Figure FDA0002650191280000042
in the calculation of S, δ — 1 for an axisymmetric configuration; for a two-dimensional planar configuration, δ — 0;
s519, Mach number M of point j is obtained j ：
Figure FDA0002650191280000043
Wherein,
Figure FDA0002650191280000044
s5110 pressure p at point j j And temperature T j Based on total temperature T 0 And total pressure p 0 And calculating according to an isentropic relation to obtain:
Figure FDA0002650191280000045
Figure FDA0002650191280000046
s5111, calculating density rho of point j by using gas state equation j ：
Figure FDA0002650191280000047
And S5112, repeating the step S511 to the step S5111, and obtaining the flow field parameters of the rest points to be obtained on the (n + 1) th grid layer.
6. The supersonic nozzle flow field and inlet parameter reconstruction method according to claim 1, wherein the step S6 specifically comprises the steps of:
s61, determining Kalman gain by adopting an ensemble Kalman filtering method:
Figure FDA0002650191280000051
wherein
Figure FDA0002650191280000052
Is a matrix X of state vectors f Relative to the sample mean
Figure FDA0002650191280000053
R is a covariance matrix of wall pressure measurements;
s62, according to
Figure FDA0002650191280000054
And (4) correcting the Mach number, the pressure and the specific heat ratio of the nozzle inlet, wherein a represents a corrected parameter.
7. A supersonic velocity spray tube flow field and the reverse rapid reconstruction device of the inlet flow parameters thereof are characterized by comprising:
a calculation grid division module for dividing calculation grids aiming at the spray pipe and dividing the Mach number M of the spray pipe inlet in Pressure p in Specific heat ratio gamma and flow field parameter xi on all grid points of spray pipe i ＝(ρ i ,u i ,p i ) Form a state vector x f ＝(ξ 1 ,ξ 2 ,…,ξ m ,γ,M in ,p in ) T Where i represents a certain grid point, m represents the number of grid points, and T represents a momentMatrix transpose, f denotes the flow field state, ρ, obtained by calculating the flow field i Denotes the density, u, of grid points i i Representing the x-direction velocity component, p, at a certain grid point i i 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 l represents the number of pressure measurements;
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;
an initial sample set determining module for setting the number N of sampling points and the Mach number M at the inlet of the given nozzle in Pressure p in Sampling the initial estimation range of the specific heat ratio gamma, and determining an initial sample set of the inlet parameters of the spray pipe;
a flow field parameter preliminary solving module for solving the flow field parameter according to different nozzle inlet Mach numbers M in the initial sample set in Pressure p in And the specific heat ratio gamma is combined, the flow field parameters of the spray pipe are solved based on a reverse characteristic line method, the flow field parameters of the initial spray pipe are obtained, the flow field parameters of the initial spray pipe comprise speed, density and pressure, and a matrix X containing state vectors of all samples is obtained f ＝(x f(1) x f(2) … x f(N) )；
A parameter correction module for correcting the Mach number M of the nozzle inlet in Pressure p in Correcting the specific heat ratio gamma;
the flow field parameter iterative computation module is used for iterating again based on the corrected nozzle inlet Mach number and pressure until the nozzle inlet Mach number M in Pressure p in And when the difference between the specific heat ratio gamma and the last iteration step is less than a set threshold value, the Mach number M of the spray pipe inlet according to convergence in Pressure p in And calculating the specific heat ratio gamma to obtain a spray pipe flow field parameter corresponding to the wall pressure of the spray pipe.
8. A storage medium comprising a stored program, wherein the program when executed controls a device on which the storage medium is located to perform the supersonic nozzle flow field and inlet parameter reconstruction method of any one of claims 1 to 6.
9. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor implements the supersonic nozzle flow field and inlet parameter reconstruction method of any one of claims 1 to 6 when executing the program.
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