CN105760600A - Method for determining heat power consumption of satellite-borne active phased-array antenna assembly based on electromechanical coupling - Google Patents
Method for determining heat power consumption of satellite-borne active phased-array antenna assembly based on electromechanical coupling Download PDFInfo
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Abstract
The invention discloses a method for determining heat power consumption of a satellite-borne active phased-array antenna assembly based on electromechanical coupling. The method includes the steps that a structure parameter, a material attribute and an electromagnetic parameter of an antenna are determined; a heat parameter of the T/R assembly is determined; the antenna array element phase center is determined; an antenna heat model is set up, heat load and boundary conditions are applied, and the antenna temperature field distribution in a space environment is calculated; the heat unit type is converted; an antenna structure finite element model is set up, a temperature load and structural constraint are applied, and antenna array face heat deformation is calculated; an antenna phase reference point is determined, array element phase center node displacement is extracted, and gain loss of the deformed antenna is calculated based on an electromechanical coupling model; whether the gain loss exceeds the allowed range or not is judged, and the heat parameter of the T/R assembly is modified; the maximum value of heat power consumption of the T/R assembly is determined. Heat power consumption of the satellite-borne active phased-array antenna assembly can be effectively determined, design of the satellite-borne active phased-array antenna assembly is guided, and assembly position layout can be guided according to antenna structure temperature field distribution.
Description
Technical field
The invention belongs to antenna technical field, specifically based on the spaceborne active phase array antenna component heat power consumption defining method of mechanical-electric coupling.Can be used for determining the maximum of spaceborne active phase array antenna component heat power consumption, it is also possible to predict antenna electric performance according to component heat power consumption, antenna module design and layout are had directive significance.
Background technology
Since the 1950's, along with the rapid development of satellite antenna, the performance requirements such as sky line multi-function, multiband, remote, high power is more and more higher.And demand small-bore, that low-gain antenna cannot realize big data transmission capacity, spaceborne active phase phased array obtains research widely and application since then.
The each irradiator of active phase array antenna is equipped with transmitting/receiving unit (i.e. T/R assembly), each antenna can produce, receive electromagnetic wave, so array antenna structure can include thousands of heater members, heat produced by its work acts on antenna structure can make front deform.Additionally, the performance of T/R assembly can be subject to variations in temperature to change.And in spaceborne environment, it is impossible to antenna structure is dispelled the heat and temperature consistency design, therefore the impact of antenna self heat production and environment extreme temperature, thermal gradient, flatness and the electrical property of the front of antenna can be had a strong impact on.Research electrical property affected about spaceborne active phase array antenna thermal deformation mainly includes two big classes: the 1. calculating of thermal deformation.As at document Wei Juan virtue, Guan Fuling, Zhao outstanding personality etc. the thermal deformation analysis of Test of Space Micro-Strip Array Antenna and experimental verification [J]. China's Space science and technology, 2002, in 6:63-68, author have studied the thermal deformation analysis of borne array antenna by setting up stretching-bending coupling effect mechanical equation, and this is that spaceborne microstrip antenna array antenna is carried out thermal deformation experiment by China first.2. electrical property calculates.Research in this respect adopts numerical method to solve, such as document VerpoorteJ, SchippersH, VosG.Technologyforconformalload-bearingantennasonaircraf tstructures [J] .2000. adopts the directional diagram after numerical calculations Test of Space Micro-Strip Array array antenna deformation, and process is loaded down with trivial details, consuming time.In a word, said method all can not directly estimate the component heat power consumption size influence degree to electrical property.Often there is a heat power consumption, just need to carry out a large amount of calculating and just can obtain the electrical property of antenna.
Therefore, it is necessary to determine the maximum of the component heat power consumption of spaceborne active phase array antenna based on electromechanical Coupling Model, it is possible not only to predict its impact on electrical property, also antenna module layout is had directive significance.
Summary of the invention
Based on the problems referred to above, the invention provides the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling, the method is based on electromechanical Coupling Model, the spaceborne active phase array antenna front thermal deformation that the heating of T/R assembly causes directly is connected with antenna electric performance, the T/R component heat power consumption affecting laws to antenna electric performance can be specified by analyzing, and then the maximum of T/R component heat power consumption can be obtained, assembly design and structural design are all had directive significance.
The technical solution realizing the present invention is, based on the spaceborne active phase array antenna component heat power consumption defining method of mechanical-electric coupling, the method comprises the steps:
(1) according to the Service Environment of spaceborne active phase array antenna and job requirement, it is determined that the structural parameters of spaceborne active phase array antenna, material properties and electromagnetic parameter；
(2) job requirement according to spaceborne active phase array antenna, it is determined that the thermal parameter of T/R assembly bottom active installing plate；
(3) electromagnetic parameter according to spaceborne active phase array antenna, it is determined that array element phase center；
(4) spaceborne active phase array antenna thermal model is set up according to the structural parameters of spaceborne active phase array antenna, material properties；
(5) thermal parameter according to spaceborne active phase array antenna, applies thermal force in FEM (finite element) model, calculates the antenna temperature field distribution under space environment；
(6) transition heat cell type is corresponding structural unit types, sets up antenna structure FEM (finite element) model, it is determined that array element phase center node；Temperature loading is put on antenna structure FEM (finite element) model, calculates the thermal deformation of spaceborne active phase array antenna front；
(7) according to spaceborne active phase array antenna front thermal deformation, array element phase center modal displacement is extracted；
(8) structural parameters according to spaceborne active phase array antenna, it is determined that the phase reference point of spaceborne active phase array antenna, utilize the array element phase center modal displacement extracted, and calculate the gain loss of deformed aerial based on electromechanical Coupling Model；
(9) judge that whether the gain loss of spaceborne active phase array antenna is beyond allowed band, without beyond allowed band, then being undertaken by step (10), otherwise go to step (11)；
(10) gain loss according to spaceborne active phase array antenna, utilizes T/R component heat power consumption, it is determined that the variable quantity of T/R component heat power consumption, the thermal parameter of amendment T/R assembly, updates antenna thermal model, goes to step (5)；
(11) T/R component heat power consumption maximum is determined.
The structural parameters of described step (1) spaceborne active phase array antenna include antenna element, substrate, active installing plate, the length of T/R assembly, width and height and the line number of antenna alignment, columns and unit interval；Described active installing plate includes aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel；Described material properties includes elastic modelling quantity, Poisson's ratio, density, heat conductivity and thermal coefficient of expansion；The thermal parameter of described spaceborne active phase array antenna refers to the heat power consumption Q of T/R assembly；The electromagnetic parameter of described spaceborne active phase array antenna includes the form of antenna element and the operating frequency f of antenna.
Described step (3), for tactical rule bay, it is determined that the geometric center of array element is the phase center of spaceborne active phase array antenna array element.
Described step (4) is set up the thermal model of spaceborne active phase array antenna and is carried out according to following steps:
(4a) according to step (3), hard spot is set at array element phase center place；
(4b) in ANSYS, set up the thermal model of antenna, aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel and T/R assembly.
Described step (5) calculates the thermo parameters method of spaceborne active phase array antenna and carries out according to following steps:
(5a) thermal boundary condition is determined: spaceborne active phase array antenna and surrounding are without heat convection, it is determined that thermal boundary condition is adiabatic environment；
(5b) heat power consumption of the thermal boundary condition and T/R assembly that apply spaceborne active phase array antenna carries out temperature field analysis in ANSYS, obtains the thermo parameters method of antenna structure.
Described step (6) calculates the front thermal deformation of spaceborne active phase array antenna and carries out according to following steps:
(6a) transition heat cell type is corresponding structural unit types, sets up the structural finite element model of spaceborne active phase array antenna, and determines the node of array element phase center；
(6b) node temperature that temperature field analysis obtains is put on antenna structure FEM (finite element) model；
(6c) apply structural constraint, calculate antenna array thermal deformation.
Described step (7) spaceborne active phase array antenna has M × N number of antenna element, and the antenna element number in x direction and the y direction orthogonal with x direction in M and N respectively antenna mounting plane, array element distance is dx×dy.According to bay phase center Node extraction, (m, n) (1≤m≤M, 1≤n≤N) individual array element is at displacement (the Δ x in x, y, z directionmn,Δymn,Δzmn)。
Described step (8) calculates the gain loss after spaceborne active phase array antenna deforms and carries out according to following steps:
(8a) determine array antenna phase reference point O according to the spread pattern of spaceborne active phase array antenna, set up coordinate system O-xyz；
(8b) according to the theory of array antenna, gain when calculating spaceborne active phase array antenna perfect condition is Gideal；
(8c) calculate the gain of point of observation P (θ, φ) place deformed aerial, realize especially by following method:
Array element phase center modal displacement (the Δ x obtained 8c-1) is extracted according to step (7)mn,Δymn,Δzmn), calculate after antenna array deformation the (m, n) individual array element is compared to the array antenna phase reference point O space quadrature produced, and formula is as follows:
In formula, Δ x11、Δy11、Δz11The respectively displacement in x, y, the z direction of phase reference point O place array element；cosαx、cosαy、cosαzRespectively point of observation P (θ, φ) and the direction cosines between coordinate axes x, y, z, are specifically expressed as follows:
In formula, θ, the angle of pitch of φ respectively given viewpoint and azimuth；
8c-2) based on electromechanical Coupling Model, calculating the field strength pattern after the deformation of spaceborne active phase array antenna, formula is as follows:
In formula, Imn、ψmnRespectively (m, n) amplitude of individual array element exciting current and phase place, k=2 π/λ is free space wave constant；
8c-3) calculate the gain of point of observation P (θ, φ) place deformed aerial based on the field strength pattern of deformed aerial, formula is as follows:
Wherein, (θ0,φ0) refer to the greatest irradiation direction of antenna；
(8d) calculating the gain loss of deformed aerial, formula is as follows:
Δ G=G-Gideal。
Described step (9) judges whether the gain of deformed aerial carries out according to the following procedure in allowed band:
(9a) job requirement according to spaceborne active phase array antenna, it is determined that gain loss maximum is Δ Glim, namely gain loss allowed band is Δ G≤Δ Glim；
(9b) judge that deformed aerial gain loss Δ G is whether in permissible range.
In described step (10), the thermal parameter of i & lt (i >=1) amendment T/R assembly carries out according to the following procedure:
(10a) the gain loss Δ G of spaceborne active phase array antenna is calculated according to (8d) i & lti, it is determined that T/R component heat power consumption Dynamic gene ti, formula is as follows:
Wherein, A refers to the proportionality coefficient that antenna gain loses.Generally, gain loss Δ GiOnly small, therefore introduce the proportionality coefficient A suitable gain amplifier loss impact on Dynamic gene.
(10b) based on T/R component heat power consumption and Dynamic gene, it is determined that T/R component heat change of power consumption amount Δ Qi, formula is as follows:
ΔQi=ti·Qi
In formula, QiT/R component heat power consumption used is calculated for i & lt；
(10c) according to the T/R component heat change of power consumption amount determined in T/R component heat power consumption and (10b), obtaining amended T/R component heat power consumption, formula is as follows:
The present invention compared with prior art, has the following characteristics that
1. the present invention is based on electromechanical Coupling Model, causes the mathematic(al) representation between front thermal deformation and electrical property according to the heating of T/R assembly, specify that the impact on electrical property of the front thermal deformation under T/R component heat power consumption effect.Utilize different T/R component heat power consumption and the antenna gain variable quantity caused thereof, give the formula of amendment T/R component heat power consumption, finally give the maximum of component heat power consumption.The method that the present invention proposes can efficiently solve component heat power consumption in engineering and be difficult to the difficult problem determined, has construction value.
2. the present invention is compared with traditional design method, theoretical direction can not only be provided to the determination of spaceborne active phase array antenna component heat power consumption, according to antenna structure thermo parameters method, module position layout can also be adjusted, provide for spaceborne active phase array antenna structural design and instruct.
Accompanying drawing explanation
Fig. 1 is the present invention flow chart based on the spaceborne active phase array antenna component heat power consumption defining method of mechanical-electric coupling；
Fig. 2 is the structural representation of spaceborne active phase array antenna；
Fig. 3 is the FEM (finite element) model of spaceborne active phase array antenna；
Fig. 4 is the thermo parameters method cloud atlas of spaceborne active phase array antenna；
Fig. 5 is the thermal deformation cloud charts of spaceborne active phase array antenna；
Fig. 6 is object space geometrical relationship schematic diagram；
When Fig. 7 is φ=0 °, the gain pattern of spaceborne active phase array antenna；
When Fig. 8 is φ=90 °, the gain pattern of spaceborne active phase array antenna.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention will be further described
With reference to Fig. 1, the present invention, based on the spaceborne active phase array antenna component heat power consumption defining method of mechanical-electric coupling, specifically comprises the following steps that
Step 1, it is determined that the structural parameters of spaceborne active phase array antenna, material properties and electromagnetic parameter
Spaceborne active phase array antenna geometric model is as shown in Figure 2, the structural parameters of spaceborne active phase array antenna include antenna element 1, substrate 2, active installing plate (aluminum honeycomb top panel 3, aluminum honeycomb 4, aluminum honeycomb lower panel 5), the length of thermal source (T/R assembly 6), width and height and the line number of antenna alignment, columns and unit interval；Material properties includes elastic modelling quantity, Poisson's ratio, density, heat conductivity and thermal coefficient of expansion；The electromagnetic parameter of spaceborne active phase array antenna includes the form of antenna element and the operating frequency f of antenna.
Step 2, it is determined that the thermal parameter of spaceborne active phase array antenna
The thermal parameter of spaceborne active phase array antenna includes the heat power consumption Q of T/R assembly.
Step 3, it is determined that array element phase center
Electromagnetic parameter according to spaceborne active phase array antenna, for the antenna element form of tactical rule, the geometric center of array element is the phase center of array element.
Step 4, sets up spaceborne active phase array antenna thermal model
(4a) according to step 3, hard spot is set at array element phase center place；
(4b) in ANSYS, set up the thermal model of antenna, aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel and T/R assembly.
Step 5, calculates antenna temperature field distribution
(5a) thermal boundary condition is determined.Spaceborne active phase array antenna and surrounding are without heat convection, it is determined that thermal boundary condition is adiabatic environment；
(5b) heat power consumption of the thermal boundary condition and T/R assembly that apply spaceborne active phase array antenna carries out temperature field analysis in ANSYS, obtains the thermo parameters method of antenna structure.
Step 6, calculates the thermal deformation of antenna array
(6a) transition heat cell type is corresponding structural unit types, sets up the structural finite element model of spaceborne active phase array antenna, and determines the node of array element phase center；
(6b) node temperature that temperature field analysis obtains is put on antenna structure FEM (finite element) model；
(6c) apply structural constraint, calculate antenna array thermal deformation.
Step 7, extracts array element phase center modal displacement
Spaceborne active phase array antenna has M × N number of antenna element, and the antenna element number in x direction and the y direction orthogonal with x direction in M and N respectively antenna mounting plane, array element distance is dx×dy；According to bay phase center Node extraction, (m, n) (1≤m≤M, 1≤n≤N) individual array element is at displacement (the Δ x in x, y, z directionmn,Δymn,Δzmn)。
Step 8, calculates the gain loss of deformed aerial
(8a) determine array antenna phase reference point O according to the spread pattern of spaceborne active phase array antenna, set up coordinate system O-xyz；
(8b) according to the theory of array antenna, gain when calculating spaceborne active phase array antenna perfect condition is Gideal；
(8c) calculate the gain of point of observation P (θ, φ) place deformed aerial, realize especially by following method:
Array element phase center modal displacement (the Δ x obtained 8c-1) is extracted according to step (7)mn,Δymn,Δzmn), calculate after antenna array deformation the (m, n) individual array element is compared to the array antenna phase reference point O space quadrature produced, and formula is as follows:
In formula, Δ x11、Δy11、Δz11The respectively displacement in x, y, the z direction of phase reference point O place array element；cosαx、cosαy、cosαzRespectively point of observation P (θ, φ) and the direction cosines between coordinate axes x, y, z, are specifically expressed as follows:
In formula, θ, the angle of pitch of φ respectively given viewpoint and azimuth；
8c-2) based on electromechanical Coupling Model, calculating the field strength pattern after the deformation of spaceborne active phase array antenna, formula is as follows:
In formula, Imn、ψmnRespectively (m, n) amplitude of individual array element exciting current and phase place, k=2 π/λ is free space wave constant；
8c-3) calculate the gain of point of observation P (θ, φ) place deformed aerial based on the field strength pattern of deformed aerial, formula is as follows:
Wherein, (θ0,φ0) refer to the greatest irradiation direction of antenna；
(8d) calculating the gain loss of deformed aerial, formula is as follows:
Δ G=G-Gideal(5)。
Step 9, it is judged that whether deformed aerial gain is in allowed band
(9a) job requirement according to spaceborne active phase array antenna, it is determined that gain loss maximum is Δ Glim, namely gain loss allowed band is Δ G≤Δ Glim；
(9b) judge that deformed aerial gain loss Δ G is whether in permissible range.
Step 10, the thermal parameter of i & lt (i >=1) amendment T/R assembly
(10a) the gain loss Δ G of spaceborne active phase array antenna is calculated according to (8d) i & lti, it is determined that T/R component heat power consumption Dynamic gene ti, formula is as follows:
Wherein, A refers to the proportionality coefficient that antenna gain loses.Generally, gain loss Δ GiOnly small, therefore introduce the proportionality coefficient A suitable gain amplifier loss impact on Dynamic gene；
(10b) based on T/R component heat power consumption and Dynamic gene, it is determined that T/R component heat change of power consumption amount Δ Qi, formula is as follows:
ΔQi=ti·Qi
In formula, QiT/R component heat power consumption used is calculated for i & lt；
(10c) according to the T/R component heat change of power consumption amount determined in T/R component heat power consumption and (10b), obtaining amended T/R component heat power consumption, formula is as follows:
Advantages of the present invention can be further illustrated by following emulation experiment:
One, the structural parameters of spaceborne active phase array antenna, thermal parameter and electromagnetic parameter are determined
The microstrip antenna that this example is 2.45GHZ with mid frequency, array number M=5, y direction, x direction array number N=5, arrangement pitches is dx×dyThe spaceborne active phase array antenna of=60mm × 60mm composition is object.Its structural parameters, material properties are as shown in Table 1 and Table 2.
The structural parameters of the spaceborne active phase array antenna of table 1
The material properties of the spaceborne active phase array antenna of table 2
Two, the thermal parameter of spaceborne active phase array antenna is determined
Job requirement according to spaceborne active phase array antenna, it is determined that the heat power consumption Q=2W of T/R assembly.
Three, the gain loss of deformed aerial is calculated
1. determine the phase center of array element
The present embodiment object of study is the microstrip antenna of tactical rule, the electromagnetic parameter according to spaceborne active microstrip antenna, it is determined that the phase center of array element is the geometric center of rectangular microstrip antenna.
2. set up the thermal model of spaceborne active phase array antenna
Hard spot is set up at array element phase center place, according to the structural parameters of spaceborne active phase array antenna, material properties and thermal parameter, ANSYS adopt SOLID278 and SHELL131 set up the thermal model of antenna, aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel and T/R assembly, as shown in Figure 3.
3. calculate spaceborne active phase array antenna thermo parameters method
Spaceborne active phase array antenna and surrounding are without heat convection, and the heat power consumption Q of the thermal boundary condition and T/R assembly that apply spaceborne active phase array antenna carries out temperature field analysis in ANSYS, obtains the thermo parameters method of antenna structure, as shown in Figure 4.
4. calculate spaceborne active phase array antenna thermal deformation distribution
(4a) transition heat cell type SOLID278 and SHELL131 is corresponding structural unit types SOLID185 and SHELL181, sets up the structural finite element model of spaceborne active phase array antenna, and determines the node of array element phase center；
(4b) node temperature that temperature field analysis obtains is put on antenna structure FEM (finite element) model；
(4c) and apply structural constraint, the thermal deformation of antenna array is calculated.As shown in Figure 5；
(4d) according to antenna array thermal deformation and array element phase center Node extraction, (m, n) displacement in x, y, z direction of (1≤m≤5,1≤n≤5) the individual array element is (Δ xmn,Δymn,Δzmn)。
5. calculate the gain loss of deformed aerial
(5a) determine array antenna phase reference point O according to the spread pattern of spaceborne active phase array antenna, set up coordinate system O-xyz；
(5b) according to the theory of array antenna, gain G during spaceborne active phase array antenna perfect condition is calculatedideal=15dB；
(5c) calculate the gain of point of observation P (θ, φ) place deformed aerial, realize especially by following method:
Array element phase center modal displacement (the Δ x obtained 5c-1) is extracted according to step (7)mn,Δymn,Δzmn), calculate after antenna array deformation the (m, n) individual array element is compared to the array antenna phase reference point O space quadrature produced, and formula is as follows:
In formula, Δ x11、Δy11、Δz11The respectively displacement in x, y, the z direction of phase reference point O place array element；Fig. 6 show the space geometry relation schematic diagram of point of observation；cosαx、cosαy、cosαzRespectively point of observation P (θ, φ) and the direction cosines between coordinate axes x, y, z, are specifically expressed as follows:
In formula, θ, the angle of pitch of φ respectively given viewpoint and azimuth；
5c-2) based on electromechanical Coupling Model, calculating the field strength pattern after the deformation of spaceborne active phase array antenna, formula is as follows:
In formula, Imn、ψmnRespectively (m, n) amplitude of individual array element exciting current and phase place, k=2 π/λ is free space wave constant；Fig. 7 and Fig. 8 show the antenna pattern of spaceborne active phase array antenna；
5c-3) calculate the gain of point of observation P (θ, φ) place deformed aerial based on the field strength pattern of deformed aerial, formula is as follows:
Wherein, (θ0,φ0) refer to the greatest irradiation direction of antenna；
(5d) calculating the gain loss of deformed aerial, formula is as follows:
Δ G=G-Gideal。
Four, the heat power consumption of T/R assembly is determined
1. the job requirement according to spaceborne active phase array antenna, it is determined that antenna gain loss allowed band Δ G≤Δ Glim=0.5dB；
2., according to above-mentioned steps, calculating the gain after the deformation of spaceborne active phase array antenna is 14.95dB, and corresponding gain loss is 0.02dB, it is seen that antenna gain loses without departing from its allowed band；
3. according to formula (4)～(5), taking the random number between A=[500,1000], calculate the heat power consumption of amended T/R assembly, repeat the above steps, acquired results is as shown in table 3.
The antenna gain of table 3T/R component heat power consumption and correspondence
From table 3 it is observed that according to spaceborne active phased array component heat power consumption defining method, after 7 times calculate, antenna gain is 14.48dB, and during with antenna perfect condition, the difference of gain is 0.52dB, beyond gain loss allowed band, therefore stop calculating.Take the maximum that the 5th step result of calculation is T/R component heat power consumption.Therefore the maximum finally giving T/R component heat power consumption is 3.72W.
From above-mentioned emulation experiment it can be seen that the method for the application present invention, can be used for the determination of spaceborne active phase array antenna component heat power consumption.Utilize the electromechanical Coupling Model of array antenna, it is possible to the impact on antenna electric performance of the front thermal deformation under clear and definite T/R component heat power consumption effect, and then utilize T/R assembly difference heat power consumption and gain loss thereof, establish the iterative formula that can revise T/R component heat power consumption.Repeatedly calculated by iterative formula, finally determine the maximum of T/R component heat power consumption.The determination of spaceborne active phase array antenna component heat power consumption is not only provided theoretical direction by the present invention, moreover it is possible to according to antenna structure thermo parameters method, module position layout is provided and instructs.
Claims (10)
1. based on the spaceborne active phase array antenna component heat power consumption defining method of mechanical-electric coupling, it is characterised in that comprise the steps:
(1) according to the Service Environment of spaceborne active phase array antenna and job requirement, it is determined that the structural parameters of spaceborne active phase array antenna, material properties and electromagnetic parameter；
(2) job requirement according to spaceborne active phase array antenna, it is determined that the thermal parameter of T/R assembly bottom active installing plate；
(3) electromagnetic parameter according to spaceborne active phase array antenna, it is determined that array element phase center；
(4) spaceborne active phase array antenna thermal model is set up according to the structural parameters of spaceborne active phase array antenna, material properties；
(5) thermal parameter according to spaceborne active phase array antenna, applies thermal force in FEM (finite element) model, calculates the antenna temperature field distribution under space environment；
(6) transition heat cell type is corresponding structural unit types, sets up antenna structure FEM (finite element) model, it is determined that array element phase center node；Temperature loading is put on antenna structure FEM (finite element) model, calculates the thermal deformation of spaceborne active phase array antenna front；
(7) according to spaceborne active phase array antenna front thermal deformation, array element phase center modal displacement is extracted；
(8) structural parameters according to spaceborne active phase array antenna, it is determined that the phase reference point of spaceborne active phase array antenna, utilize the array element phase center modal displacement extracted, and calculate the gain loss of deformed aerial based on electromechanical Coupling Model；
(9) judge that whether the gain loss of spaceborne active phase array antenna is beyond allowed band, without beyond allowed band, then being undertaken by step (10), otherwise go to step (11)；
(10) gain loss according to spaceborne active phase array antenna, utilizes T/R component heat power consumption, it is determined that the variable quantity of T/R component heat power consumption, the thermal parameter of amendment T/R assembly, updates antenna thermal model, goes to step (5)；
(11) T/R component heat power consumption maximum is determined.
2. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterized in that, in described step (1), the structural parameters of spaceborne active phase array antenna include antenna element, substrate, active installing plate and the length of T/R assembly, width and height and the line number of antenna alignment, columns and unit interval；Described active installing plate includes aluminum honeycomb top panel, aluminum honeycomb and aluminum honeycomb lower panel；Described material properties includes elastic modelling quantity, Poisson's ratio, density, heat conductivity and thermal coefficient of expansion；The thermal parameter of described spaceborne active phase array antenna refers to the heat power consumption Q of T/R assembly；The electromagnetic parameter of described spaceborne active phase array antenna includes the form of antenna element and the operating frequency f of antenna.
3. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterized in that, in described step (3), for tactical rule bay, it is determined that the geometric center of array element is the phase center of spaceborne active phase array antenna array element.
4. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterised in that described step (4) carries out according to the following procedure:
(4a) according to step (3), hard spot is set at array element phase center place；
(4b) in ANSYS, set up the thermal model of antenna, aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel and T/R assembly.
5. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterised in that described step (5) carries out according to the following procedure:
(5a) thermal boundary condition is determined: spaceborne active phase array antenna and surrounding are without heat convection, it is determined that thermal boundary condition is adiabatic environment；
(5b) heat power consumption of the thermal boundary condition and T/R assembly that apply spaceborne active phase array antenna carries out temperature field analysis in ANSYS, obtains the thermo parameters method of antenna structure.
6. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterised in that described step (6) carries out according to the following procedure:
(6a) transition heat cell type is corresponding structural unit types, sets up the structural finite element model of spaceborne active phase array antenna, and determines the node of array element phase center；
(6b) node temperature that temperature field analysis obtains is put on antenna structure FEM (finite element) model；
(6c) apply structural constraint, calculate antenna array thermal deformation.
7. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterized in that, in described step (7), if spaceborne active phase array antenna has M × N number of array element, the element number of array in x direction and the y direction orthogonal with x direction in M and N respectively antenna mounting plane, array element distance is dx×dy；According to bay phase center Node extraction, (m, n) displacement in x, y, z direction of the individual array element is (Δ xmn,Δymn,Δzmn), wherein, 1≤m≤M, 1≤n≤N.
8. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterised in that described step (8) carries out according to the following procedure:
(8a) determine phase reference point O according to the spread pattern of spaceborne active phase array antenna, set up coordinate system O-xyz；
(8b) according to the theory of array antenna, gain when calculating spaceborne active phase array antenna perfect condition is Gideal；
(8c) calculate the gain loss of point of observation P (θ, φ) place deformed aerial, realize especially by following method:
Array element phase center modal displacement (the Δ x obtained 8c-1) is extracted according to step (7)mn,Δymn,Δzmn), (m, n) individual array element is compared to the reference point O space quadrature produced to calculate after antenna array deformation the
In formula, Δ x11、Δy11、Δz11The respectively displacement in x, y, the z direction of phase reference point O place array element；cosαx、cosαy、cosαzRespectively point of observation P (θ, φ) and the direction cosines between coordinate axes x, y, z, are specifically expressed as follows:
In formula, θ, the angle of pitch of φ respectively given viewpoint and azimuth；
8c-2) based on electromechanical Coupling Model, calculate the field strength pattern E (θ, φ) after the deformation of spaceborne active phase array antenna:
In formula, Imn、ψmnRespectively (m, n) amplitude of individual array element exciting current and phase place, k=2 π/λ is free space wave constant；
8c-3) based on the field strength pattern of deformed aerial, calculate the gain G of point of observation P (θ, φ) place deformed aerial:
Wherein, (θ0,φ0) refer to the greatest irradiation direction of antenna；
(8d) the gain loss Δ G of deformed aerial is calculated:
Δ G=G-Gideal。
9. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterized in that, in described step (9), the job requirement according to spaceborne active phase array antenna, it is determined that gain loss maximum is Δ Glim, namely gain loss allowed band is Δ G≤Δ Glim。
10. the spaceborne active phase array antenna component heat power consumption defining method based on mechanical-electric coupling according to claim 1, it is characterised in that in described step (10), the thermal parameter of i & lt amendment T/R assembly carries out according to the following procedure:
(10a) the gain loss Δ G of spaceborne active phase array antenna is calculated according to (8d) i & lti, it is determined that T/R component heat power consumption Dynamic gene ti:
Wherein, A refers to the proportionality coefficient that antenna gain loses；i≥1；
(10b) based on T/R component heat power consumption and Dynamic gene, it is determined that T/R component heat change of power consumption amount Δ Qi:
ΔQi=ti·Qi
In formula, QiT/R component heat power consumption used is calculated for i & lt；
(10c) according to the T/R component heat change of power consumption amount determined in T/R component heat power consumption and (10b), amended T/R component heat power consumption is obtained:
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