CN105760600B - Method is determined based on the spaceborne active phase array antenna component heat power consumption of mechanical-electric coupling - Google Patents

Method is determined based on the spaceborne active phase array antenna component heat power consumption of mechanical-electric coupling Download PDF

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CN105760600B
CN105760600B CN201610089283.0A CN201610089283A CN105760600B CN 105760600 B CN105760600 B CN 105760600B CN 201610089283 A CN201610089283 A CN 201610089283A CN 105760600 B CN105760600 B CN 105760600B
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antenna
active phase
array antenna
heat power
spaceborne active
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CN105760600A (en
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王从思
毛静
王艳
王伟
宋立伟
程景胜
朱敏波
陈光达
保宏
米建伟
李申
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Xidian Univ
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    • GPHYSICS
    • G06COMPUTING; CALCULATING; COUNTING
    • G06FELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00Computer-aided design [CAD]
    • G06F30/20Design optimisation, verification or simulation
    • G06F30/23Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • GPHYSICS
    • G06COMPUTING; CALCULATING; COUNTING
    • G06FELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00Computer-aided design [CAD]
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    • G06F30/36Circuit design at the analogue level
    • G06F30/367Design verification, e.g. using simulation, simulation program with integrated circuit emphasis [SPICE], direct methods or relaxation methods

Abstract

The invention discloses the spaceborne active phase array antenna component heat power consumptions based on mechanical-electric coupling to determine method, including:Determine antenna structure parameter, material properties and electromagnetic parameter;Determine T/R component thermal parameters;Determine bay phase center;Antenna thermal model is established, thermal force and boundary condition are applied, calculates the antenna temperature field distribution under space environment;Transition heat cell type establishes antenna structure finite element model, applies temperature loading and structural constraint, calculates antenna array thermal deformation;It determines antenna phase reference point, extracts array element phase center modal displacement, the gain loss of deformed aerial is calculated based on electromechanical Coupling Model;Allowable range is seen if fall out, the thermal parameter of T/R components is changed;Determine T/R component heat power consumption maximum values.The present invention can effectively determine the heat power consumption of spaceborne active phase array antenna component, not only design the component of spaceborne active phase array antenna and provide guidance, can be also laid out to module position according to antenna structure thermo parameters method and provide guidance.

Description

Method is determined based on the spaceborne active phase array antenna component heat power consumption of mechanical-electric coupling
Technical field
The invention belongs to antenna technical fields, specifically the spaceborne active phase array antenna component hot merit based on mechanical-electric coupling Consumption determines method.It can be used for determining the maximum value of spaceborne active phase array antenna component heat power consumption, it can also be according to component hot merit Consumption prediction antenna electric performance, designing antenna module and being laid out has directive significance.
Background technology
Since the 1950s, with the rapid development of satellite antenna, to day line multi-function, multiband, long distance It is higher and higher from performance requirements such as, high powers.And small-bore, low-gain antenna cannot achieve the need of big data transmission capacity It asks, spaceborne active phase phased array has obtained extensive research and application since then.
The each radiator of active phase array antenna is equipped with transmitting/receiving unit (i.e. T/R components), and each antenna can It generates, receive electromagnetic wave, so array antenna structure can include thousands of heating device, heat caused by work Acting on antenna structure can make front deform.In addition, the performance of T/R components can be changed by temperature change.And spaceborne In environment, heat dissipation and temperature consistency design can not be carried out to antenna structure, therefore antenna itself heat production and environment extreme temperature, The influence of thermal gradient can seriously affect the flatness and electrical property of the front of antenna.About spaceborne active phase array antenna thermal change Shape includes mainly two major classes on the research that electrical property influences:1. the calculating of thermal deformation.Such as in document Wei Juan virtues, Guan Fuling, people Zhao The thermal deformation analysis and experimental verification [J] China's Space science and technology of the Test of Space Micro-Strip Array Antenna such as outstanding person, 2002,6:In 63-68, Author has studied the thermal deformation analysis of borne array antenna by establishing stretching-bending coupling effect mechanical equation, this be China for the first time Thermal deformation experiment is carried out to spaceborne microstrip antenna array antenna.2. electrical property calculates.Research mostly uses numerical method progress in this respect It solves, such as document Verpoorte J, Schippers H, Vos G.Technology for conformal load- Bearing antennas on aircraft structures [J] .2000. is using numerical calculations Test of Space Micro-Strip Array The deformed directional diagram of array antenna, process are cumbersome, time-consuming.In short, the above method all cannot directly estimate component heat power consumption size To the influence degree of electrical property.Often there are one heat power consumption, just need to carry out largely calculating the electrical property that can just obtain 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 Value, can not only predict its influence to electrical property, also have directive significance to antenna module layout.
Invention content
Based on the above issues, the present invention provides the spaceborne active phase array antenna component heat power consumption based on mechanical-electric coupling is true Determine method, this method is based on electromechanical Coupling Model, spaceborne active phase array antenna front thermal deformation caused by T/R components are generated heat It is directly connected with antenna electric performance, affecting laws of the T/R components heat power consumption to antenna electric performance can be specified by analysis, And then the maximum value of T/R component heat power consumptions can be obtained, all there is directive significance to component design and structure design.
Realize that technical solution of the invention is the spaceborne active phase array antenna component heat power consumption based on mechanical-electric coupling Determine that method, this method include the following steps:
(1) according to the Service Environment of spaceborne active phase array antenna and job requirement, spaceborne active phase array antenna is determined Structural parameters, material properties and electromagnetic parameter;
(2) according to the job requirement of spaceborne active phase array antenna, the physochlaina infudibularis of active mounting plate bottom T/R components is determined Number;
(3) according to the electromagnetic parameter of spaceborne active phase array antenna, array element phase center is determined;
(4) spaceborne active phase array antenna heat is established according to the structural parameters of spaceborne active phase array antenna, material properties Model;
(5) according to the thermal parameter of spaceborne active phase array antenna, apply thermal force on finite element model, calculate space ring Antenna temperature field distribution under border;
(6) transition heat cell type is corresponding structural unit types, establishes antenna structure finite element model, determines array element Phase center node;Temperature loading is applied to antenna structure finite element model, calculates spaceborne active phase array antenna front Thermal deformation;
(7) according to spaceborne active phase array antenna front thermal deformation, array element phase center modal displacement is extracted;
(8) according to the structural parameters of spaceborne active phase array antenna, the phase reference of spaceborne active phase array antenna is determined Point calculates the gain loss of deformed aerial based on electromechanical Coupling Model using the array element phase center modal displacement of extraction;
(9) judge whether the gain loss of spaceborne active phase array antenna exceeds allowable range, if without departing from permission Range can then be carried out by step (10), otherwise go to step (11);
(10) T/R component heat is determined using T/R component heat power consumptions according to the gain loss of spaceborne active phase array antenna The variable quantity of power consumption changes the thermal parameter of T/R components, updates antenna thermal model, goes to step (5);
(11) T/R component heat power consumption maximum values are determined.
The structural parameters of the spaceborne active phase array antenna of the step (1) include antenna element, substrate, active mounting plate, Length, width and the height of T/R components and line number, columns and the cell spacing of antenna alignment;The active mounting plate includes Aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel;The material properties include elasticity modulus, Poisson's ratio, density, heat conduction system Number and coefficient of thermal expansion;The thermal parameter of the spaceborne active phase array antenna refers to the heat power consumption Q of T/R components;It is described spaceborne active The electromagnetic parameter of phased array antenna includes the form of antenna element and the working frequency f of antenna.
The step (3) determines that the geometric center of array element is spaceborne active phase for the bay of tactical rule The phase center of array antenna array element.
The thermal model that the step (4) establishes spaceborne active phase array antenna follows the steps below:
Hard spot is arranged according to step (3) in (4a) at array element phase center;
(4b) establishes the hot-die of antenna, aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel and T/R components in ANSYS Type.
The thermo parameters method that the step (5) calculates spaceborne active phase array antenna follows the steps below:
(5a) determines thermal boundary condition:Spaceborne active phase array antenna, without heat convection, determines thermal boundary with ambient enviroment Condition is adiabatic environment;
(5b) applies the thermal boundary condition of spaceborne active phase array antenna and the heat power consumption of T/R components carries out in ANSYS Temperature field analysis obtains the thermo parameters method of antenna structure.
The front thermal deformation that the step (6) calculates spaceborne active phase array antenna follows the steps below:
(6a) transition heat cell type is corresponding structural unit types, and the structure for establishing spaceborne active phase array antenna has Meta-model is limited, and determines the node of array element phase center;
The node temperature that temperature field analysis obtains is applied to antenna structure finite element model by (6b);
(6c) applies structural constraint, calculates antenna array thermal deformation.
The spaceborne active phase array antenna of the step (7) shares M × N number of antenna element, and M and N are respectively that antenna installation is flat The antenna element number in the directions x and the y direction orthogonal with the directions x in face, array element spacing are dx×dy.According to bay phase Centroid extracts (m, n) (1≤m≤M, 1≤n≤N) a array element in x, y, displacement (the Δ x in the directions zmn,Δymn,Δzmn)。
The step (8) calculates the spaceborne deformed gain loss of active phase array antenna and follows the steps below:
(8a) determines array antenna phase reference point O according to the spread pattern of spaceborne active phase array antenna, establishes coordinate It is O-xyz;
(8b) according to the theory of array antenna, gain when calculating spaceborne active phase array antenna perfect condition is Gideal
(8c) calculates the gain of deformed aerial at point of observation P (θ, φ), is realized especially by following methods:
Obtained array element phase center modal displacement (Δ x 8c-1) is extracted according to step (7)mn,Δymn,Δzmn), it calculates (m, n) a array element is compared to the space quadrature that array antenna phase reference point O is generated after antenna array deformation, and formula is such as Under:
In formula, Δ x11、Δy11、Δz11The x of array element, y, the displacement in the directions z at respectively phase reference point O;cosαx、 cosαy、cosαzRespectively point of observation P (θ, φ) and the direction cosines between reference axis x, y, z are specific to indicate as follows:
In formula, θ, φ are respectively pitch angle and the azimuth of given viewpoint;
It 8c-2) is based on electromechanical Coupling Model, calculates the deformed field strength pattern of spaceborne active phase array antenna, formula is such as Under:
In formula, Imn、ψmnThe respectively amplitude and phase of (m, n) a array element exciting current, k=2 π/λ are free space Wave constant;
8c-3) field strength pattern based on deformed aerial calculates to obtain the gain of deformed aerial, formula at point of observation P (θ, φ) It is as follows:
Wherein, (θ00) refer to the greatest irradiation direction of antenna;
(8d) calculates the gain loss of deformed aerial, and formula is as follows:
Δ G=G-Gideal
Judge whether the gain of deformed aerial carries out according to the following procedure within the allowable range in the step (9):
(9a) determines that gain loss maximum value is Δ G according to the job requirement of spaceborne active phase array antennalim, i.e. gain Loss allowable range is Δ G≤Δ Glim
Whether (9b) judges deformed aerial gain loss Δ G in permissible range.
The thermal parameter of ith (i >=1) modification T/R components carries out according to the following procedure in the step (10):
(10a) according to (8d) ith calculate spaceborne active phase array antenna gain loss Δ Gi, determine T/R components Heat power consumption Dynamic gene ti, formula is as follows:
Wherein, A refers to the proportionality coefficient of antenna gain loss.Generally, gain loss Δ GiVery little, therefore introduce proportionality coefficient A Appropriate gain amplifier loses the influence to Dynamic gene.
(10b) is based on T/R components heat power consumption and Dynamic gene, determines T/R component heat power consumption variation deltas Qi, formula is such as Under:
ΔQi=ti·Qi
In formula, QiT/R component heat power consumptions used are calculated for ith;
(10c) is obtained modified according to the T/R component heat power consumption variable quantities determined in T/R components heat power consumption and (10b) T/R component heat power consumptions, formula are as follows:
Compared with prior art, the present invention having the characteristics that:
1. the present invention is based on electromechanical Coupling Model, the number between front thermal deformation and electrical property is caused according to the fever of T/R components Expression formula is learned, specifies influence of the front thermal deformation under the effect of T/R component heat power consumptions to electrical property.Utilize different T/R components Heat power consumption and its caused antenna gain variable quantity give the formula of modification T/R component heat power consumptions, finally obtain component hot merit The maximum value of consumption.Method proposed by the present invention can efficiently solve component heat power consumption in engineering and be difficult to determining problem, have work Journey is worth.
2. the present invention, can not only be to the determination of spaceborne active phase array antenna component heat power consumption compared with traditional design method Theoretical direction is provided, module position layout can also be adjusted according to antenna structure thermo parameters method, be spaceborne active phased array day Cable architecture design provides guidance.
Description of the drawings
Fig. 1 is that the present invention is based on the flows that the spaceborne active phase array antenna component heat power consumption of mechanical-electric coupling determines method Figure;
Fig. 2 is the structural schematic diagram of spaceborne active phase array antenna;
Fig. 3 is the 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.
Specific implementation mode
The present invention will be further described with reference to the accompanying drawings and embodiments
Referring to Fig.1, the present invention is based on the spaceborne active phase array antenna component heat power consumptions of mechanical-electric coupling to determine method, specifically Steps are as follows:
Step 1, the structural parameters, material properties and electromagnetic parameter of spaceborne active phase array antenna are determined
As shown in Figure 2, the structural parameters of spaceborne active phase array antenna include spaceborne active phase array antenna geometrical model Antenna element 1, substrate 2, active mounting plate (aluminum honeycomb top panel 3, aluminum honeycomb 4, aluminum honeycomb lower panel 5), heat source (T/R components 6) line number, columns and the cell spacing of length, width and height and antenna alignment;Material properties include elasticity modulus, pool Loose ratio, density, thermal coefficient and coefficient of thermal expansion;The electromagnetic parameter of spaceborne active phase array antenna includes the form of antenna element With the working frequency f of antenna.
Step 2, the thermal parameter of spaceborne active phase array antenna is determined
The thermal parameter of spaceborne active phase array antenna includes the heat power consumption Q of T/R components.
Step 3, array element phase center is determined
According to the electromagnetic parameter of spaceborne active phase array antenna, for the antenna element form of tactical rule, array element it is several What center is the phase center of array element.
Step 4, spaceborne active phase array antenna thermal model is established
Hard spot is arranged according to step 3 in (4a) at array element phase center;
(4b) establishes the hot-die of antenna, aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel and T/R components in ANSYS Type.
Step 5, antenna temperature field distribution is calculated
(5a) determines thermal boundary condition.Spaceborne active phase array antenna, without heat convection, determines thermal boundary with ambient enviroment Condition is adiabatic environment;
(5b) applies the thermal boundary condition of spaceborne active phase array antenna and the heat power consumption of T/R components carries out in ANSYS Temperature field analysis obtains the thermo parameters method of antenna structure.
Step 6, the thermal deformation of antenna array is calculated
(6a) transition heat cell type is corresponding structural unit types, and the structure for establishing spaceborne active phase array antenna has Meta-model is limited, and determines the node of array element phase center;
The node temperature that temperature field analysis obtains is applied to antenna structure finite element model by (6b);
(6c) applies structural constraint, calculates antenna array thermal deformation.
Step 7, array element phase center modal displacement is extracted
Spaceborne active phase array antenna shares M × N number of antenna element, M and N be respectively in antenna mounting plane the directions x and The antenna element number in the y direction orthogonal with the directions x, array element spacing are dx×dy;According to bay phase center Node extraction (m, n) (1≤m≤M, 1≤n≤N) a array element is in x, y, displacement (the Δ x in the directions zmn,Δymn,Δzmn)。
Step 8, the gain loss of deformed aerial is calculated
(8a) determines array antenna phase reference point O according to the spread pattern of spaceborne active phase array antenna, establishes coordinate It is O-xyz;
(8b) according to the theory of array antenna, gain when calculating spaceborne active phase array antenna perfect condition is Gideal
(8c) calculates the gain of deformed aerial at point of observation P (θ, φ), is realized especially by following methods:
Obtained array element phase center modal displacement (Δ x 8c-1) is extracted according to step (7)mn,Δymn,Δzmn), it calculates (m, n) a array element is compared to the space quadrature that array antenna phase reference point O is generated after antenna array deformation, and formula is such as Under:
In formula, Δ x11、Δy11、Δz11The x of array element, y, the displacement in the directions z at respectively phase reference point O;cosαx、 cosαy、cosαzRespectively point of observation P (θ, φ) and the direction cosines between reference axis x, y, z are specific to indicate as follows:
In formula, θ, φ are respectively pitch angle and the azimuth of given viewpoint;
It 8c-2) is based on electromechanical Coupling Model, calculates the deformed field strength pattern of spaceborne active phase array antenna, formula is such as Under:
In formula, Imn、ψmnThe respectively amplitude and phase of (m, n) a array element exciting current, k=2 π/λ are free space Wave constant;
8c-3) field strength pattern based on deformed aerial calculates to obtain the gain of deformed aerial, formula at point of observation P (θ, φ) It is as follows:
Wherein, (θ00) refer to the greatest irradiation direction of antenna;
(8d) calculates the gain loss of deformed aerial, and formula is as follows:
Δ G=G-Gideal (5)。
Step 9, judge deformed aerial gain whether within the allowable range
(9a) determines that gain loss maximum value is Δ G according to the job requirement of spaceborne active phase array antennalim, i.e. gain Loss allowable range is Δ G≤Δ Glim
Whether (9b) judges deformed aerial gain loss Δ G in permissible range.
Step 10, the thermal parameter of ith (i >=1) modification T/R components
(10a) according to (8d) ith calculate spaceborne active phase array antenna gain loss Δ Gi, determine T/R components Heat power consumption Dynamic gene ti, formula is as follows:
Wherein, A refers to the proportionality coefficient of antenna gain loss.Generally, gain loss Δ GiVery little, therefore introduce proportionality coefficient A Appropriate gain amplifier loses the influence to Dynamic gene;
(10b) is based on T/R components heat power consumption and Dynamic gene, determines T/R component heat power consumption variation deltas Qi, formula is such as Under:
ΔQi=ti·Qi
In formula, QiT/R component heat power consumptions used are calculated for ith;
(10c) is obtained modified according to the T/R component heat power consumption variable quantities determined in T/R components heat power consumption and (10b) T/R component heat power consumptions, formula are as follows:
Advantages of the present invention can be further illustrated by following emulation experiment:
One, structural parameters, thermal parameter and the electromagnetic parameter of spaceborne active phase array antenna are determined
This example is the microstrip antenna of 2.45GHZ with centre frequency, the directions x array number M=5, the directions y array number N=5, Arrangement spacing is dx×dyThe spaceborne active phase array antenna of=60mm × 60mm compositions is object.Its structural parameters, material properties As shown in Table 1 and Table 2.
The structural parameters of 1 spaceborne active phase array antenna of table
The material properties of 2 spaceborne active phase array antenna of table
Two, the thermal parameter of spaceborne active phase array antenna is determined
According to the job requirement of spaceborne active phase array antenna, the heat power consumption Q=2W of T/R components is determined.
Three, the gain loss of deformed aerial is calculated
1. determining the phase center of array element
The present embodiment research object is the microstrip antenna of tactical rule, according to the electromagnetic parameter of spaceborne active microstrip antenna, Determine that the phase center of array element is the geometric center of rectangular microstrip antenna.
2. establishing the thermal model of spaceborne active phase array antenna
Establish hard spot at array element phase center, according to the structural parameters of spaceborne active phase array antenna, material properties and Thermal parameter, in ANSYS using SOLID278 and SHELL131 establish antenna, aluminum honeycomb top panel, aluminum honeycomb, below aluminum honeycomb The thermal model of plate and T/R components, as shown in Figure 3.
3. calculating spaceborne active phase array antenna thermo parameters method
Spaceborne active phase array antenna, without heat convection, applies the thermal boundary of spaceborne active phase array antenna with ambient enviroment The heat power consumption Q of condition and T/R components carries out temperature field analysis in ANSYS, obtains the thermo parameters method of antenna structure, such as Fig. 4 It is shown.
4. calculating spaceborne active phase array antenna thermal deformation distribution
(4a) transition heat cell type SOLID278 and SHELL131 be corresponding structural unit types SOLID185 and SHELL181 establishes the structural finite element model of spaceborne active phase array antenna, and determines the node of array element phase center;
The node temperature that temperature field analysis obtains is applied to antenna structure finite element model by (4b);
(4c) and apply structural constraint, calculates the thermal deformation of antenna array.As shown in Figure 5;
(4d) is according to antenna array thermal deformation and array element phase center Node extraction (m, n) (1≤m≤5,1≤n≤5) For a array element in x, the displacement of y, the directions z are (Δ xmn,Δymn,Δzmn)。
5. calculating the gain loss of deformed aerial
(5a) determines array antenna phase reference point O according to the spread pattern of spaceborne active phase array antenna, establishes coordinate It is O-xyz;
(5b) calculates gain G when spaceborne active phase array antenna perfect condition according to the theory of array antennaideal= 15dB;
(5c) calculates the gain of deformed aerial at point of observation P (θ, φ), is realized especially by following methods:
Obtained array element phase center modal displacement (Δ x 5c-1) is extracted according to step (7)mn,Δymn,Δzmn), it calculates (m, n) a array element is compared to the space quadrature that array antenna phase reference point O is generated after antenna array deformation, and formula is such as Under:
In formula, Δ x11、Δy11、Δz11The x of array element, y, the displacement in the directions z at respectively phase reference point O;Shown in Fig. 6 For the space geometry relation schematic diagram of point of observation;cosαx、cosαy、cosαzRespectively point of observation P (θ, φ) and reference axis x, y, z Between direction cosines, it is specific to indicate as follows:
In formula, θ, φ are respectively pitch angle and the azimuth of given viewpoint;
It 5c-2) is based on electromechanical Coupling Model, calculates the deformed field strength pattern of spaceborne active phase array antenna, formula is such as Under:
In formula, Imn、ψmnThe respectively amplitude and phase of (m, n) a array element exciting current, k=2 π/λ are free space Wave constant;Fig. 7 and Fig. 8 show the antenna pattern of spaceborne active phase array antenna;
5c-3) field strength pattern based on deformed aerial calculates to obtain the gain of deformed aerial, formula at point of observation P (θ, φ) It is as follows:
Wherein, (θ00) refer to the greatest irradiation direction of antenna;
(5d) calculates the gain loss of deformed aerial, and formula is as follows:
Δ G=G-Gideal
Four, the heat power consumption of T/R components is determined
1. according to the job requirement of spaceborne active phase array antenna, antenna gain loss allowable range Δ G≤Δ G is determinedlim =0.5dB;
2. according to above-mentioned steps, calculate the deformed gain of spaceborne active phase array antenna is 14.95dB, corresponding increasing Benefit loss is 0.02dB, it is seen that antenna gain is lost without departing from its allowable range;
3. according to formula (4)~(5), the random number between A=[500,1000] is taken, calculates the heat of modified T/R components Power consumption repeats the above steps, and acquired results are as shown in table 3.
3 T/R components heat power consumption of table and corresponding antenna gain
From table 3 it is observed that method is determined according to spaceborne active phased array component heat power consumption, and after 7 times calculate, day Line gain is 14.48dB, and the difference with gain when antenna perfect condition is 0.52dB, has exceeded gain loss allowable range, therefore Stop calculating.It is the maximum value of T/R component heat power consumptions to take the 5th step result of calculation.Therefore finally obtain T/R components heat power consumption most Big value is 3.72W.
The method using the present invention is can be seen that from above-mentioned emulation experiment, can be used for spaceborne active phase array antenna component The determination of heat power consumption.Using the electromechanical Coupling Model of array antenna, the front thermal change under the effect of T/R component heat power consumptions can be specified Influence of the shape to antenna electric performance, and then T/R component difference heat power consumptions and its gain loss are utilized, T/R groups can be changed by establishing The iterative formula of part heat power consumption.It is calculated repeatedly by iterative formula, the final maximum value for determining T/R component heat power consumptions.The present invention Not only theoretical direction is provided to determining for spaceborne active phase array antenna component heat power consumption, moreover it is possible to according to antenna structure temperature field point Cloth is laid out module position and provides guidance.

Claims (9)

1. the spaceborne active phase array antenna component heat power consumption based on mechanical-electric coupling determines method, which is characterized in that including following Step:
(1) according to the Service Environment of spaceborne active phase array antenna and job requirement, the knot of spaceborne active phase array antenna is determined Structure parameter, material properties and electromagnetic parameter;
(2) according to the job requirement of spaceborne active phase array antenna, the thermal parameter of active mounting plate bottom T/R components is determined;
(3) according to the electromagnetic parameter of spaceborne active phase array antenna, array element phase center is determined;
(4) spaceborne active phase array antenna thermal model is established according to the structural parameters of spaceborne active phase array antenna, material properties;
(5) according to the thermal parameter of spaceborne active phase array antenna, apply thermal force on finite element model, calculate under space environment Antenna temperature field distribution;
(6) transition heat cell type is corresponding structural unit types, establishes antenna structure finite element model, determines array element phase Centroid;Temperature loading is applied to antenna structure finite element model, calculates the thermal change of spaceborne active phase array antenna front Shape;
(7) according to spaceborne active phase array antenna front thermal deformation, array element phase center modal displacement is extracted;
(8) according to the structural parameters of spaceborne active phase array antenna, the phase reference point of spaceborne active phase array antenna is determined, profit With the array element phase center modal displacement of extraction, the gain loss of deformed aerial is calculated based on electromechanical Coupling Model;
(9) judge whether the gain loss of spaceborne active phase array antenna exceeds allowable range, if without departing from allowable range, It can then be carried out by step (10), otherwise go to step (11);
(10) T/R component heat power consumptions are determined using T/R component heat power consumptions according to the gain loss of spaceborne active phase array antenna Variable quantity, change T/R components thermal parameter, update antenna thermal model, go to step (5);
(11) T/R component heat power consumption maximum values are determined;
In the step (10), the thermal parameter of ith modification T/R components carries out according to the following procedure:
(10a) according to ith calculate spaceborne active phase array antenna gain loss Δ Gi, determine that T/R component heat power consumptions adjust Factor ti
Wherein, GidealRefer to gain when antenna perfect condition, A refers to the proportionality coefficient of antenna gain loss;i≥1;
Wherein, the gain loss Δ G=G-G of deformed aerial is calculatedideal, G is the gain of deformed aerial at point of observation P (θ, φ);
(10b) is based on T/R components heat power consumption and Dynamic gene, determines T/R component heat power consumption variation deltas Qi
ΔQi=ti·Qi
In formula, QiT/R component heat power consumptions used are calculated for ith;
(10c) obtains modified T/R according to the T/R component heat power consumption variable quantities determined in T/R components heat power consumption and (10b) Component heat power consumption:
2. the spaceborne active phase array antenna component heat power consumption according to claim 1 based on mechanical-electric coupling determines method, It is characterized in that, in the step (1), the structural parameters of spaceborne active phase array antenna include antenna element, substrate, active peace The loading board and length of T/R components, the line number of width and height and antenna alignment, columns and cell spacing;The active installation Plate includes aluminum honeycomb top panel, aluminum honeycomb and aluminum honeycomb lower panel;The material properties include elasticity modulus, Poisson's ratio, density, Thermal coefficient and coefficient of thermal expansion;The thermal parameter of the spaceborne active phase array antenna refers to the heat power consumption Q of T/R components;The star The electromagnetic parameter for carrying active phase array antenna includes the form of antenna element and the working frequency f of antenna.
3. the spaceborne active phase array antenna component heat power consumption according to claim 1 based on mechanical-electric coupling determines method, It is characterized in that, in the step (3), for the bay of tactical rule, determine that the geometric center of array element has to be spaceborne The phase center of source phased array antenna array element.
4. the spaceborne active phase array antenna component heat power consumption according to claim 1 based on mechanical-electric coupling determines method, It is characterized in that, the step (4) carries out according to the following procedure:
Hard spot is arranged according to step (3) in (4a) at array element phase center;
(4b) establishes the thermal model of antenna, aluminum honeycomb top panel, aluminum honeycomb, aluminum honeycomb lower panel and T/R components in ANSYS.
5. the spaceborne active phase array antenna component heat power consumption according to claim 1 based on mechanical-electric coupling determines method, It is characterized in that, the step (5) carries out according to the following procedure:
(5a) determines thermal boundary condition:Spaceborne active phase array antenna, without heat convection, determines thermal boundary condition with ambient enviroment For adiabatic environment;
(5b) apply spaceborne active phase array antenna thermal boundary condition and T/R components heat power consumption in ANSYS into trip temperature Field analysis obtains the thermo parameters method of antenna structure.
6. the spaceborne active phase array antenna component heat power consumption according to claim 1 based on mechanical-electric coupling determines method, It is characterized in that, the step (6) carries out according to the following procedure:
(6a) transition heat cell type is corresponding structural unit types, establishes the structure finite element of spaceborne active phase array antenna Model, and determine the node of array element phase center;
The node temperature that temperature field analysis obtains is applied to antenna structure finite element model by (6b);
(6c) applies structural constraint, calculates antenna array thermal deformation.
7. the spaceborne active phase array antenna component heat power consumption according to claim 1 based on mechanical-electric coupling determines method, It is characterized in that, in the step (7), if spaceborne active phase array antenna shares M × N number of array element, M and N are respectively antenna peace The element number of array in the directions x and the y direction orthogonal with the directions x in plane is filled, array element spacing is dx×dy;According to bay phase Centroid extracts (m, n) a array element in x, and the displacement of y, the directions z are (Δ xmn,Δymn,Δzmn), wherein 1≤m≤M, 1 ≤n≤N。
8. the spaceborne active phase array antenna component heat power consumption according to claim 1 based on mechanical-electric coupling determines method, It is characterized in that, the step (8) carries out according to the following procedure:
(8a) determines phase reference point O according to the spread pattern of spaceborne active phase array antenna, establishes 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) calculates the gain loss of deformed aerial at point of observation P (θ, φ), is realized especially by following methods:
Obtained array element phase center modal displacement (Δ x 8c-1) is extracted according to step (7)mn,Δymn,Δzmn), calculate antenna (m, n) a array element is compared to the space quadrature that reference point O is generated after wavefront distortion
In formula, Δ x11、Δy11、Δz11The x of array element, y, the displacement in the directions z at respectively phase reference point O;cosαx、cosαy、 cosαzRespectively point of observation P (θ, φ) and the direction cosines between reference axis x, y, z are specific to indicate as follows:
In formula, θ, φ are respectively pitch angle and the azimuth of given viewpoint;
It 8c-2) is based on electromechanical Coupling Model, calculates the deformed field strength pattern E (θ, φ) of spaceborne active phase array antenna:
In formula, Imn、ψmnThe respectively amplitude and phase of (m, n) a array element exciting current, k=2 π/λ are that free space wave is normal Number;
8c-3) the field strength pattern based on deformed aerial calculates to obtain the gain G of deformed aerial at point of observation P (θ, φ):
Wherein, (θ00) refer to the greatest irradiation direction of antenna;
(8d) calculates the gain loss Δ G of deformed aerial:
Δ G=G-Gideal
9. the spaceborne active phase array antenna component heat power consumption according to claim 1 based on mechanical-electric coupling determines method, It is characterized in that, in the step (9), according to the job requirement of spaceborne active phase array antenna, gain loss maximum value is determined For Δ Glim, i.e. gain loss allowable range is Δ G≤Δ Glim
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