CN106469850B - A kind of Thickness Design Method of antenna house - Google Patents
A kind of Thickness Design Method of antenna house Download PDFInfo
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- H—ELECTRICITY
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Abstract
The present invention relates to a kind of Thickness Design Method of antenna house, include the following steps: that the thickness of antenna house is carried out discretization according to the short transverse of cover by (1)；(2) it determines the value range of thickness value, and initial value is assigned to the thickness at discrete point；(3) according to the thickness value at discrete point, its statistical value is calculated, (4) calculate the far field of antenna, and therefrom extract gain G1With main beam position B1These electrical performance indexes；(5) transmission coefficient of cover is calculated with transmission line theory, (6) calculate the far field F ' (θ, φ) with cover antenna system, draw far-field pattern, (7) establish mathematical optimization models；(8) whether the electrical performance indexes and thickness distribution for judging the antenna house obtained after optimization meet preset requirement.It improves the electrical performance indexes of antenna house.
Description
Technical Field
The invention belongs to the technical field of radar antennas, and particularly relates to a thickness design method of an antenna housing, which can be used for structural design of an aircraft antenna housing.
Background
The radome is a wave-transparent shell for protecting the antenna from the natural environment, and is a specially-shaped electromagnetic transparent window formed by a covering made of natural or artificial dielectric materials or a dielectric shell supported by a truss. The antenna housing with the excellent design has the functions of protectiveness, conductivity, reliability, concealment, decoration and the like, and can prolong the service life of each part of the whole system, reduce the service life cost and the operation cost, simplify the design, reduce the maintenance cost, ensure the accuracy of the surface and the position of the antenna, and create a good working environment for an antenna operator. However, the radome also affects the electromagnetic radiation of the desired antenna, which may reduce the electrical performance of the desired antenna.
Aircraft radome often adopts streamlined cover body in order to satisfy aerodynamic requirement to lead to the antenna house to the electrical property influence of inside antenna too big, need carry out optimal design in order to improve its electrical property to the antenna house. The traditional equal-thickness optimization technology has a limited degree of improving the electrical performance of the antenna housing, and the thickness of the antenna housing is discretized along the height direction of the housing body, so that the thickness-variable optimization design is performed, and the electrical performance of the streamline housing body can be greatly improved.
Fanxue ping optimizes aiming errors of a two-dimensional phased array antenna housing by using a genetic algorithm in a paper 'optimization of aiming errors of the two-dimensional antenna housing based on the genetic algorithm' 2011, wall thickness values of all areas are used as optimization variables by dividing the wall thickness of the antenna housing into different areas along the height direction in an equal length mode, the maximum aiming error in the antenna scanning process is used as an optimization target, and the optimal wall thickness distribution is solved by using the genetic algorithm, so that the aiming errors of the antenna housing are effectively reduced. The method has the following defects: the restriction on the wall thickness distribution is not considered, so that the wall thickness of the obtained radome changes violently and is difficult to process and realize, and the important electrical performance index of the gain loss of the radome is not considered.
Disclosure of Invention
The invention aims to provide a thickness design method of an antenna housing, which can improve the electrical performance index of the antenna housing and reduce the manufacturing difficulty of the antenna housing aiming at the defects of the prior art.
In order to achieve the purpose, the technical scheme of the invention is as follows: a thickness design method of an antenna housing comprises the following steps:
(1) discretizing the thickness of the antenna housing according to the height direction of the housing body;
establishing a coordinate system O-xyz by taking the bottom surface center of the radome as an origin and the bottom surface as an xy plane along the height of the radome, uniformly selecting 10 discrete points along the direction along the height of the radome along the z direction, and recording the coordinates as z1,z2,…,z10；
(2) Determining the value range of the thickness value according to the requirements of the structural performance and the electrical performance of the antenna housing, and assigning an initial value to the thickness at the discrete point;
(3) and calculating the statistic values of the thickness values at the discrete points, including the variance, the maximum slope and the variance of the slope.
(4) Calculating the far field of the antenna and extracting the gain G therefrom1And main beam position B1These electrical properties are indicative.
(5) Calculating the transmission coefficient of the cover body by using a transmission line theory according to the structural parameters and the material parameters of the antenna coverAnd according to the known antenna aperture field E (x, y), calculating the aperture field after penetrating through the antenna housing:
(6) calculating the far field F '(theta, phi) of the antenna system with the radome according to the aperture field E' (x, y) after the antenna radome is penetrated, drawing a far field directional diagram, and extracting the gain G from the far field directional diagram2And main beam position B2These electrical performance metrics, in turn, determine the radome induced gain loss TL and the pointing error BSE.
(7) Establishing an optimal design model by taking the thickness value at the discrete point in the step (1) as a design variable, the variance of the thickness, the maximum slope, the variance of the slope in the step (3) and the electrical performance index in the step (6) as design targets, and solving the model by using a particle swarm optimization algorithm to obtain the thickness distribution of the radome;
(8) and (3) judging whether the electrical performance index and the thickness distribution of the antenna housing obtained after optimization meet preset requirements, if so, judging that the antenna housing structural design scheme is qualified, otherwise, modifying the discretization method and the optimization algorithm parameters of the antenna housing, and repeating the steps (1) to (8) until obtaining the design scheme that the electrical performance index and the thickness distribution meet the preset requirements.
And (2) determining the value range of the thickness value according to the requirements of the structural performance and the electrical performance of the antenna housing, and performing the following steps:
(2a) an integrally formed aircraft radome generally adopts a half-wavelength wall thickness, and the calculation formula of the half-wavelength wall thickness is as follows:
where λ is the wavelength, ∈rIs the relative dielectric constant of the radome material and α is the angle of incidence of the incident electromagnetic wave on the radome wall.
(2b) N is determined according to the structural performance requirement of the cover body, the larger n is, the thicker the cover wall is, the better the structural performance is, and meanwhile, the poorer the electrical performance is, so that the minimum n value capable of meeting the structural performance requirement is taken.
(2c) The minimum value α of the angle of incidence of the electromagnetic wave radiated by the antenna on the shield wall during scanning of the internal antenna is calculatedminAnd maximum value αmax。
(2d) Determining the minimum value d of the thickness value according to the following formulaminAnd maximum value dmax：
The step (4) is realized by the following steps:
(4a) respectively representing the components in the x, y and z directions of the coordinate system established in the step (1) by i, j and k, and calculating the far-field value F (theta, phi) of the antenna according to the known antenna aperture field distribution E (x, y):
wherein theta and phi are the spherical coordinate angles of the observation point in O-xyz,λ is the wavelength of the antenna, according to the antenna operating frequency f and the speed of light c, by the formulaCalculating to obtain s as the area of the integral unit;
(4b) drawing an antenna far-field directional diagram according to the far-field F (theta, phi) of the ideal antenna, and extracting the gain G from the directional diagram1And main beam position B1These electrical properties are indicative.
The step (5) is realized by the following steps:
(5a) regarding the coordinate system established in the step (1), the x, y and z direction components are respectively represented by i, j and k, and the known antenna aperture field distribution is denoted as E (x, y).
(5b) In commercial model analysis software, a geometric model of the radome is established according to the structural form of the radome, the side length of a grid is set to be 0.2 lambda, wherein lambda is the wavelength of an antenna, and the model is subjected to grid division;
(5c) according to the structural parameters and the material parameters of the antenna housing, the transmission coefficient of each point on the covering is calculated by using the transmission line theory
(5c1) According to the geometric shape of the antenna housing and an incident aperture field, an incident angle α and a polarization angle β at each point on the antenna housing are obtained, namely, an included angle between an incident ray of electromagnetic waves and a normal line at the incident point is recorded as an incident angle α, and an included angle between a polarization direction of the electromagnetic waves and an incident plane is recorded as a polarization angle β, wherein the incident plane is formed by the incident ray of the electromagnetic waves and the normal line at the incident point;
(5c2) according to the thickness value d at discrete points1,d2,….,d10Obtaining a smooth thickness profile of the radome by using a cubic B spline interpolation method:
d(z)＝fcubic-B-spline(d1,...,d10)
(5c3) according to the thickness d and the relative dielectric constant epsilon of each part of the antenna housingrLoss tangent tan delta, calculating the transmission coefficient of horizontal polarization component at each point on the skinAnd vertical polarization component transmission coefficient
Wherein, ZH＝cosα，these parameters are all intermediate variables; t isH、TVAre respectively asModulus of (d), ηH、ηVAre respectively asThe phase of (d);
(5c4) transmission coefficient according to horizontal polarization componentAnd vertical polarization component transmission coefficientObtaining the transmission coefficient of the main polarization component:
wherein,is an intermediate variable;
(5d) multiplying the aperture field incident on the antenna housing by the transmission coefficient of the corresponding point, and calculating the aperture field after penetrating the skin:
the step (6) is realized by the following steps:
(6a) calculating a far field F '(θ, Φ) generated by the aperture field after passing through the radome according to the aperture field E' (x, y) after passing through the radome obtained in the step (1) by the following formula:
where θ and φ are spherical coordinate angles of the observation point in the rectangular coordinate system O-xyz, and k0For free space propagation constant, by formulaCalculating, lambda is the wavelength of the antenna, according to the working frequency f and the speed of light c of the antenna, through a formulaCalculating to obtain s as the area of the integral unit;
(6b) drawing a far-field directional diagram of the covered antenna according to a far-field F' (theta, phi) generated by a caliber field penetrating through the antenna cover, and extracting a gain G from the directional diagram2And main beam position B2These electrical performance metrics;
(6c) calculating gain loss TL and aiming error BSE caused by the antenna housing according to the electrical performance indexes calculated in the step (4) and the step (5):
TL＝G1－G2
BSE＝|B1－B2|
the step (7) is realized by the following steps:
(7a) and (3) establishing an aircraft radome variable thickness optimization model considering thickness control by taking the thickness value at the discrete point in the step (1) as a design variable, and taking the variance of the thickness, the maximum slope and the slope in the step (3) and the gain loss and the aiming error caused by the radome in the step (6) as design targets:
wherein BSEmaxIs the maximum value of the aiming error caused by the antenna housing under all working conditions, TLmaxIs the maximum value of the gain loss caused by the radome under all working conditions, vd is the variance of the design variable, mds is the maximum value of the slope of the design variable, vds is the variance of the slope of the design variable, BSE0,TL0,vd0,mds0And vds0Is a normalized coefficient given according to a specific problem, dminIs the lower limit of the design variable, dmaxIs the upper value limit of the design variable;
(7b) and solving the aircraft radome variable thickness optimization model considering thickness control by adopting a Particle Swarm Optimization (PSO) algorithm to obtain the optimal radome thickness distribution, wherein the population scale of the PSO algorithm is taken as 50, the evolution algebra is taken as 200, the inertia weight is linearly decreased to 0.4 from 0.9 along with the evolution algebra, and the acceleration constant is taken as 2.
According to the antenna housing, due to the fact that the thickness control factor is introduced, and the gain loss of the antenna housing is considered, compared with the existing variable thickness design method, the antenna housing has the advantages that the electrical performance index of the antenna housing is improved, and the manufacturing difficulty of the antenna housing is reduced.
Drawings
FIG. 1 is a general flow chart of an implementation of the present invention;
FIG. 2 is a sub-flowchart of the present invention for calculating the aperture field after passing through the radome;
FIG. 3 is a schematic view of an antenna and radome relationship for use with the present invention;
FIG. 4 is a schematic structural diagram of an aircraft radome for use in simulation of the present invention;
FIG. 5 is a comparative plot of pointing error before and after the optimum design of an aircraft radome using the present invention;
FIG. 6 is a graph comparing gain loss before and after the optimum design of an aircraft radome using the present invention;
fig. 7 is a comparison of thickness distributions obtained before and after the optimal design of an aircraft radome using the present invention.
Detailed Description
The present invention is described in further detail below with reference to the attached drawings.
Referring to fig. 1, the method comprises the following specific steps:
and (1) discretizing the thickness of the antenna housing according to the height direction of the housing body.
As shown in fig. 2, a coordinate system O-xyz is established along the height of the cover body by taking the center of the bottom surface of the radome as an origin and the bottom surface as an xy plane, the height of the cover body along the z direction uniformly selects 10 discrete points along the direction, and the coordinates of the discrete points are recorded as z1,z2,…,z10In the figure thetasRepresenting the scan angle of the antenna.
And (2) determining the value range of the thickness value, and assigning an initial value to the thickness at the discrete point.
(2a) An integrally formed aircraft radome generally adopts a half-wavelength wall thickness, and the calculation formula of the half-wavelength wall thickness is as follows:
where λ is the wavelength, ∈rIs the relative dielectric constant of the radome material and α is the angle of incidence of the incident electromagnetic wave on the radome wall.
(2b) N is determined according to the structural performance requirement of the cover body, the larger n is, the thicker the cover wall is, the better the structural performance is, and meanwhile, the poorer the electrical performance is, so that the minimum n value capable of meeting the structural performance requirement is taken.
(2c) The minimum value α of the angle of incidence of the electromagnetic wave radiated by the antenna on the shield wall during scanning of the internal antenna is calculatedminAnd maximum value αmax。
(2d) Determining the minimum value d of the thickness value according to the following formulaminAnd maximum value dmax：
(2e) In the interval [ dmin,dmax]And (3) randomly selecting a group of numbers as the thickness values of the discrete points in the step (1).
Step (3), calculating the variance, the maximum slope and the variance of the slope according to the thickness value at the discrete point;
according to the thickness value d at discrete points1,d2,….,d10The variance vd of these numbers is calculated and further based on its coordinates z1,z2,…,z10Calculating the slope values of the adjacent discrete points:
the maximum value mds of these slope values and its variance vds are calculated.
Step (4), calculating the far field of the antenna and extracting the gain G from the far field1And main beam position B1These electrical performance metrics;
(4a) respectively representing the components in the x, y and z directions of the coordinate system established in the step (1) by i, j and k, and calculating the far-field value F (theta, phi) of the antenna according to the known antenna aperture field distribution E (x, y):
wherein theta and phi are the spherical coordinate angles of the observation point in O-xyz,λ is the wavelength of the antenna, according to the antenna operating frequency f and the speed of light c, by the formulaCalculating to obtain s as the area of the integral unit;
(4b) drawing an antenna far-field directional diagram according to the far-field F (theta, phi) of the ideal antenna, and extracting the gain G from the directional diagram1And main beam position B1These electrical properties are indicative.
Step (5), calculating the transmission coefficient of the cover body by using a transmission line theory according to the structural parameters and the material parameters of the antenna coverAnd according to the known antenna aperture field E (x, y), calculating the aperture field after penetrating through the antenna housing:
referring to fig. 3, the specific implementation of this step is as follows:
(5a) regarding the coordinate system established in the step (1), the x, y and z direction components are respectively represented by i, j and k, and the known antenna aperture field distribution is denoted as E (x, y).
(5b) In commercial model analysis software, a geometric model of the radome is established according to the structural form of the radome, the side length of a grid is set to be 0.2 lambda, wherein lambda is the wavelength of an antenna, and the model is subjected to grid division;
(5c) according to the structural parameters and the material parameters of the antenna housing, the transmission coefficient of each point on the covering is calculated by using the transmission line theory
(5c1) According to the geometric shape of the antenna housing and an incident aperture field, an incident angle α and a polarization angle β at each point on the antenna housing are obtained, namely, an included angle between an incident ray of electromagnetic waves and a normal line at the incident point is recorded as an incident angle α, and an included angle between a polarization direction of the electromagnetic waves and an incident plane is recorded as a polarization angle β, wherein the incident plane is formed by the incident ray of the electromagnetic waves and the normal line at the incident point;
(5c2) according to the thickness value d at discrete points1,d2,….,d10Obtaining a smooth thickness profile of the radome by using a cubic B spline interpolation method:
d(z)＝fcubic-B-spline(d1,...,d10)
(5c3) according to the thickness d and the relative dielectric constant epsilon of each part of the antenna housingrLoss tangent tan delta, calculating the transmission coefficient of horizontal polarization component at each point on the skinAnd vertical polarization component transmission coefficient
Wherein, ZH＝cosα，these parameters are all intermediate variables; t isH、TVAre respectively asModulus of (d), ηH、ηVAre respectively asThe phase of (d);
(5c4) transmission coefficient according to horizontal polarization componentAnd vertical polarization component transmission coefficientObtaining the transmission coefficient of the main polarization component:
wherein,is an intermediate variable;
(5d) multiplying the aperture field incident on the antenna housing by the transmission coefficient of the corresponding point, and calculating the aperture field after penetrating the skin:
step (6), according to the aperture field E '(x, y) after penetrating through the antenna cover, calculating the far field F' (theta, phi) of the antenna with the cover, drawing a far field directional diagram, and extracting the gain G from the far field directional diagram2And main beam position B2These electrical performance metrics, in turn, determine the radome induced gain loss TL and the pointing error BSE.
(6a) Calculating a far field F '(θ, Φ) generated by the aperture field after passing through the radome according to the aperture field E' (x, y) after passing through the radome obtained in the step (1) by the following formula:
where θ and φ are spherical coordinate angles of the observation point in the rectangular coordinate system O-xyz, and k0For free space propagation constant, by formulaCalculating, lambda is the wavelength of the antenna, according to the working frequency f and the speed of light c of the antenna, through a formulaAnd calculating to obtain s as the area of the integral unit.
(6b) Drawing a far-field directional diagram of the covered antenna according to a far-field F' (theta, phi) generated by a caliber field penetrating through the antenna cover, and extracting a gain G from the directional diagram2And main beam position B2These electrical properties are indicative.
(6c) Calculating gain loss TL and aiming error BSE caused by the antenna housing according to the electrical performance indexes calculated in the step (4) and the step (5):
TL＝G1－G2
BSE＝|B1－B2|
and (7) establishing and solving an optimization design model.
(7a) And (3) establishing an aircraft radome variable thickness optimization model considering thickness control by taking the thickness value at the discrete point in the step (1) as a design variable, and taking the variance of the thickness, the maximum slope and the slope in the step (3) and the gain loss and the aiming error caused by the radome in the step (6) as design targets:
wherein BSEmaxIs the maximum value of the aiming error caused by the antenna housing under all working conditions, TLmaxIs the maximum value of the gain loss caused by the radome under all working conditions, vd is the variance of the design variable, mds is the maximum value of the slope of the design variable, vds is the variance of the slope of the design variable, BSE0,TL0,vd0,mds0And vds0Is a normalized coefficient given according to a specific problem, dminIs the lower limit of the design variable, dmaxIs the upper value limit of the design variable.
(7b) And solving the aircraft radome variable thickness optimization model considering thickness control by adopting a Particle Swarm Optimization (PSO) algorithm to obtain the optimal radome thickness distribution. The population scale of the particle swarm optimization algorithm is 50, the evolution algebra is 200, the inertia weight is linearly decreased to 0.4 from 0.9 along with the evolution algebra, and the acceleration constant is 2.
And (8) judging whether the electrical performance index and the thickness distribution of the antenna housing obtained after optimization meet preset requirements.
Judging whether the electrical performance index change amount of a system after the radome is added and the radome is subjected to optimized design and the thickness distribution of the radome meet preset requirements or not according to the electrical performance index change amount allowed by the antenna, and if so, judging that the radome structural design scheme is qualified; and otherwise, modifying the discretization method and the optimization parameters of the antenna housing, and repeating the steps (1) to (8) until the result meets the requirement.
The advantages of the present invention can be further illustrated by the following simulation experiments:
1. simulation parameters
The shape of an aircraft radome is shown in fig. 4, the diameter of the bottom surface of the radome is 0.5 meter, the height of the radome is 1 meter, the radome is made of glass fiber reinforced plastic, the relative dielectric constant of the material is 4, the magnetic loss tangent is 0.015, the aperture of an antenna in the radome is 0.22 meter, the working frequency is 9.4GHz, the aperture field of the antenna is in constant-amplitude and in-phase distribution, and the scanning angle range of the antenna is 0-90 degrees.
2. Simulation content and results
The aircraft radome is subjected to thickness optimization design considering thickness control by using the method, simulation results are shown in fig. 5, 6 and 7, and simulation data are shown in table 1.
In fig. 5, 6 and 7, design 1 represents an equal thickness design, design 2 represents a design obtained by a conventional variable thickness design method, and design 3 represents a design obtained by a variable thickness design method considering thickness control according to the present invention.
Table 1 electrical performance index of the system
According to the data, after the traditional variable-thickness design is adopted, the electrical performance of the antenna housing is obviously improved, but the cost is that the thickness of the antenna housing is changed violently, so that great difficulty is caused to the machining and manufacturing of the antenna housing.
The simulation data experiment proves that the electrical property of the antenna housing of the aircraft can be effectively improved, and the manufacturing difficulty of the antenna housing of the aircraft can be reduced.
Claims (6)
1. A thickness design method of an antenna housing is characterized by comprising the following steps: the method comprises the following steps:
(1) discretizing the thickness of the antenna housing according to the height direction of the housing body;
establishing a coordinate system O-xyz by taking the bottom surface center of the radome as an origin and the bottom surface as an xy plane along the height of the radome, uniformly selecting 10 discrete points along the direction along the height of the radome along the z direction, and recording the coordinates as z1,z2,…,z10；
(2) Determining the value range of the thickness value according to the requirements of the structural performance and the electrical performance of the antenna housing, and assigning an initial value to the thickness at the discrete point;
(3) calculating the statistical values including the variance, the maximum slope and the variance of the slope according to the thickness value at the discrete point, and calculating the statistical values according to the thickness value d at the discrete point1,d2,…,d10The variance vd of these numbers is calculated and further based on its coordinates z1,z2,…,z10Calculating the slope values of the adjacent discrete points:
calculating the maximum value mds of the slope values and the variance vds thereof;
(4) calculating the far field of the antenna and extracting the gain G therefrom1And main beam position B1These electrical performance metrics;
(5) calculating the transmission coefficient of the cover body by using a transmission line theory according to the structural parameters and the material parameters of the antenna coverAnd according to the known antenna aperture field E (x, y), calculating the aperture field after penetrating through the antenna housing:
(6) calculating the far field F '(theta, phi) of the antenna system with the radome according to the aperture field E' (x, y) after the antenna radome is penetrated, drawing a far field directional diagram, and extracting the gain G from the far field directional diagram2And main beam position B2The gain loss TL and the aiming error BSE caused by the antenna housing are further determined according to the electrical performance indexes;
(7) establishing an optimal design model by taking the thickness value at the discrete point in the step (1) as a design variable, the variance of the thickness, the maximum slope, the variance of the slope in the step (3) and the electrical performance index in the step (6) as design targets, and solving the model by using a particle swarm optimization algorithm to obtain the thickness distribution of the radome;
(8) and (3) judging whether the electrical performance index and the thickness distribution of the antenna housing obtained after optimization meet preset requirements, if so, judging that the antenna housing structural design scheme is qualified, otherwise, modifying the discretization method and the optimization algorithm parameters of the antenna housing, and repeating the steps (1) to (8) until obtaining the design scheme that the electrical performance index and the thickness distribution meet the preset requirements.
2. The method for designing the thickness of the radome of claim 1, wherein: and (2) determining the value range of the thickness value according to the requirements of the structural performance and the electrical performance of the antenna housing, and performing the following steps:
(2a) the integrally formed aircraft radome adopts a half-wavelength wall thickness, and the calculation formula of the half-wavelength wall thickness is as follows:
where λ is the wavelength, ∈rIs the relative dielectric constant of the radome material, α is the angle of incidence of the incident electromagnetic wave on the radome wall;
(2b) determining n according to the structural performance requirement of the cover body, wherein the larger n, the thicker the cover wall, the better the structural performance, and the poorer the electrical performance, so that the minimum n value capable of meeting the structural performance requirement is obtained;
(2c) the minimum value α of the angle of incidence of the electromagnetic wave radiated by the antenna on the shield wall during scanning of the internal antenna is calculatedminAnd maximum value αmax，
(2d) Determining the minimum value d of the thickness value according to the following formulaminAnd maximum value dmax：
3. The method for designing the thickness of the radome of claim 1, wherein: the step (4) is realized by the following steps:
(4a) respectively representing the components in the x, y and z directions of the coordinate system established in the step (1) by i, j and k, and calculating the far-field value F (theta, phi) of the antenna according to the known antenna aperture field distribution E (x, y):
wherein theta and phi are the spherical coordinate angles of the observation point in O-xyz,λ is the wavelength of the antenna, according to the antenna operating frequency f and the speed of light c, by the formulaCalculating to obtain s as the area of the integral unit;
(4b) drawing an antenna far-field directional diagram according to the far-field F (theta, phi) of the ideal antenna, and extracting the gain G from the directional diagram1And main beam position B1These electrical properties are indicative.
4. The method for designing the thickness of the radome of claim 1, wherein: the step (6) is realized by the following steps:
(5a) regarding the coordinate system established in the step (1), respectively representing components in x, y and z directions by i, j and k, and recording known antenna aperture field distribution as E (x, y);
(5b) in commercial model analysis software, a geometric model of the radome is established according to the structural form of the radome, the side length of a grid is set to be 0.2 lambda, wherein lambda is the wavelength of an antenna, and the model is subjected to grid division;
(5c) according to the structural parameters and the material parameters of the antenna housing, the transmission coefficient of each point on the covering is calculated by using the transmission line theory
(5c1) According to the geometric shape of the antenna housing and an incident aperture field, an incident angle α and a polarization angle β at each point on the antenna housing are obtained, namely, an included angle between an incident ray of electromagnetic waves and a normal line at the incident point is recorded as an incident angle α, and an included angle between a polarization direction of the electromagnetic waves and an incident plane is recorded as a polarization angle β, wherein the incident plane is formed by the incident ray of the electromagnetic waves and the normal line at the incident point;
(5c2) according to the thickness value d at discrete points1,d2,…,d10Obtaining a smooth thickness profile of the radome by using a cubic B spline interpolation method:
d(z)＝fcubic-B-spline(d1,...,d10)
(5c3) according to the thickness d and the relative dielectric constant epsilon of each part of the antenna housingrLoss tangent tan delta, calculating the transmission coefficient of horizontal polarization component at each point on the skinAnd vertical polarization component transmission coefficient
Wherein, ZH＝cosα，these parameters are all intermediate variables; t isH、TVAre respectively asModulus of (d), ηH、ηVAre respectively asThe phase of (d);
(5c4) transmission coefficient according to horizontal polarization componentAnd vertical polarization component transmission coefficientObtaining the transmission coefficient of the main polarization component:
wherein,is an intermediate variable;
(5d) multiplying the aperture field incident on the antenna housing by the transmission coefficient of the corresponding point, and calculating the aperture field after penetrating the skin:
5. the method for designing the thickness of the radome of claim 1, wherein: the step (6) is realized by the following steps:
(6a) calculating a far field F '(θ, Φ) generated by the aperture field after passing through the radome according to the aperture field E' (x, y) after passing through the radome obtained in the step (1) by the following formula:
where θ and φ are spherical coordinate angles of the observation point in the rectangular coordinate system O-xyz, and k0For free space propagation constant, by formulaCalculating, lambda is the wavelength of the antenna, according to the working frequency f and the speed of light c of the antenna, through a formulaCalculating to obtain s as the area of the integral unit;
(6b) drawing a far-field directional diagram of the covered antenna according to a far-field F' (theta, phi) generated by a caliber field penetrating through the antenna cover, and extracting a gain G from the directional diagram2And main beam position B2These electrical performance metrics;
(6c) calculating gain loss TL and aiming error BSE caused by the antenna housing according to the electrical performance indexes calculated in the step (4) and the step (5):
TL＝G1－G2
BSE＝|B1－B2|。
6. the method for designing the thickness of the radome of claim 1, wherein: the step (7) is realized by the following steps:
(7a) and (3) establishing an aircraft radome variable thickness optimization model considering thickness control by taking the thickness value at the discrete point in the step (1) as a design variable, and taking the variance of the thickness, the maximum slope and the slope in the step (3) and the gain loss and the aiming error caused by the radome in the step (6) as design targets:
wherein d ismin≤di≤dmax,i＝1,...,10
Wherein BSEmaxIs the maximum value of the aiming error caused by the antenna housing under all working conditions, TLmaxIs the maximum value of the gain loss caused by the radome under all working conditions, vd is the variance of the design variable, mds is the maximum value of the slope of the design variable, vds is the variance of the slope of the design variable, BSE0,TL0,vd0,mds0And vds0Is a normalized coefficient given according to a specific problem, dminIs the lower limit of the design variable, dmaxIs the upper value limit of the design variable;
(7b) the aircraft radome variable thickness optimization model considering thickness control is solved by adopting a particle swarm optimization algorithm to obtain the optimal radome thickness distribution, the population scale of the particle swarm optimization algorithm is 50, the evolution algebra is 200, the inertia weight is linearly decreased to 0.4 from 0.9 along with the evolution algebra, and the acceleration constant is 2.
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