CN108363884B - Method for adjusting and installing rod piece of expandable support structure of satellite-borne planar SAR (synthetic aperture radar) antenna - Google Patents

Method for adjusting and installing rod piece of expandable support structure of satellite-borne planar SAR (synthetic aperture radar) antenna Download PDF

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CN108363884B
CN108363884B CN201810188396.5A CN201810188396A CN108363884B CN 108363884 B CN108363884 B CN 108363884B CN 201810188396 A CN201810188396 A CN 201810188396A CN 108363884 B CN108363884 B CN 108363884B
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郭俊康
赵强强
余德文
赵鼎堂
洪军
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Xian Jiaotong University
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Abstract

The invention discloses a method for adjusting and installing a rod piece of an expandable support structure of a satellite-borne planar SAR antenna, which comprises the following steps of: determining geometric parameters and locking hinge stiffness parameters of the expandable support structure; establishing a deformation coordination equation of the expandable support structure, wherein the deformation coordination equation comprises a rod length coordination equation, a rod intersection point mechanical equilibrium equation and an internal and external antenna panel moment equilibrium equation; establishing an optimal adjustment basic mathematical model of the expandable support structure rod piece by taking the total deformation energy of the SAR antenna as a target function and three equations in the step S2 as constraint conditions; and (4) calculating the rod length adjustment amount through the basic mathematical model in the step S3 to finish the precise adjustment. The method is a precise quantitative digital optimization adjustment technology for the rod piece of the deployable supporting structure of the satellite-borne planar SAR antenna, which takes the minimum structural strain energy as a target function and takes a deformation coordination equation and assembly precision as constraint conditions, and realizes quantitative digital adjustment of the rod piece in the ground assembly process.

Description

Method for adjusting and installing rod piece of expandable support structure of satellite-borne planar SAR (synthetic aperture radar) antenna
Technical Field
The invention belongs to the technical field of satellite-borne planar SAR antenna adjustment and installation; in particular to a method for adjusting and installing a rod piece of an expandable support structure of a satellite-borne planar SAR antenna.
Background
The deployable supporting structure of the satellite-borne planar SAR satellite antenna has multiple ring constraints and a complex topological structure, and belongs to a typical multi-ring closed-link system structure. In order to realize the smooth expansion and normal service of the satellite-borne planar SAR satellite antenna in space, the assembly precision of the expandable support structure must be ensured in the ground assembly process. However, the pointing accuracy of the satellite antenna often exceeds the design requirements due to the influence of rod length errors, hinge assembly positioning errors and rod deformation. For this reason, engineers typically need to make rod length adjustments to the support rods during ground assembly. However, the current aerospace enterprises adopt a pure experience 'blind tuning' mode of measurement-adjustment-measurement, which not only has overlong assembly period and consumes time and labor, but also often fails to meet the requirements of assembly precision and reliable expansion of the expandable support structure. Therefore, the method for accurately and quantitatively adjusting the rods of the deployable supporting structure of the satellite-borne planar SAR satellite antenna is important for shortening the installation and adjustment period and improving the deployment reliability.
At present, domestic technologies and documents on the aspect are few and few, and no mature or existing method can be used for calculating the adjustment amount of the rods of the expandable support structure. Therefore, a quantitative optimization adjustment method suitable for the satellite-borne planar SAR satellite antenna deployable support structure rod is provided, so that the problems of overlong adjustment period, undeployed and locked engineering stubborn problems caused by 'blind adjustment' are solved.
Disclosure of Invention
The invention provides a method for adjusting and installing a rod piece of an expandable support structure of a satellite-borne planar SAR antenna; the method is a precise quantitative digital optimization adjustment technology for the rod piece of the deployable supporting structure of the satellite-borne planar SAR antenna, which takes the minimum structural strain energy as a target function and takes a deformation coordination equation and assembly precision as constraint conditions, and realizes quantitative digital adjustment of the rod piece in the ground assembly process.
The technical scheme of the invention is as follows: a method for adjusting and installing a rod piece of a deployable supporting structure of a space-borne planar SAR antenna comprises the following steps:
step S1, determining geometric parameters of the expandable support structure and rigidity parameters of the locking hinge;
step S2, establishing a deformation coordination equation of the expandable support structure, wherein the deformation coordination equation comprises a rod length coordination equation, a rod intersection point mechanical equilibrium equation and an inner and outer antenna panel moment equilibrium equation;
step S3, establishing an optimized adjustment basic mathematical model of the expandable support structure rod piece by taking the total deformation energy of the SAR antenna as a target function and the deformation coordination equation in the step S2 as a constraint condition;
and step S4, calculating the rod length adjustment quantity through the basic mathematical model in the step S3 to obtain the optimal rod length adjustment quantity combination, and finishing accurate adjustment.
Furthermore, the invention is characterized in that:
the method in which the stick length adjustment amount is calculated in step S4 is an active search method starting from a discrete variable or a variable rounding method starting from a continuous variable.
The active search method starting from the discrete variable comprises the following specific processes: generating all rod length adjustment amount combinations according to the rod length adjustment amount range and the adjustment amount interval; then combining the rod length adjustment quantities and substituting the rod length adjustment quantities into a basic mathematical model to calculate to obtain total strain energy and angle deviation of the inner antenna panel and the outer antenna panel; and selecting a plurality of rod length adjustment amount combinations meeting the index requirements, and sequencing according to the total strain energy of the rod length adjustment amount combinations to obtain the optimal rod length adjustment amount combination with the minimum total strain energy.
The specific process of the variable rounding method starting from the continuous variable is as follows: settling the optimal adjustment amount combination based on an optimization algorithm; then rounding the optimal adjustment amount combination to an actual adjustable value, and obtaining a plurality of new rod length adjustment amount combinations; combining a plurality of rod length adjustment quantities and substituting the rod length adjustment quantities into a basic mathematical model to calculate to obtain total strain energy and angle deviation of the inner antenna panel and the outer antenna panel; and selecting a plurality of rod length adjustment amount combinations meeting the index requirements, and sequencing according to the total strain energy of the rod length adjustment amount combinations to obtain the optimal rod length adjustment amount combination with the minimum total strain energy.
Wherein the load compartment and the inner and outer antenna panels of the SAR antenna are set as rigid bodies in step S1.
Wherein the coordinated rod length equation in step S2 is:
Figure GDA0002404736840000031
wherein O, D, C, B represent the actual coordinates of the end points of the expandable support structure after the coordination of the deformation, F represents the reference coordinate point [ Delta x ]f,Δyf]；lofThe design length for the rod OF; Δ lofIs the rod length deviation OF the rod OF; lofIs the amount OF deformation OF the rod OF; lofThe design length for the rod OF; Δ lofIs the rod length deviation OF the rod OF; lofIs the amount OF deformation OF the rod OF; ldfDesigning the length of the rod piece DF; Δ ldfIs a rod pieceRod length deviation of DF; ldfThe deformation of the rod piece DF; lcfThe design length for the rod CF; Δ lcfThe rod length deviation of the rod member CF; lcfThe deformation amount of the rod member CF; lbfDesigning the length of the rod BF; Δ lbfThe length deviation of the bar BF; lbfThe amount of deformation of the bar BF.
The mechanical equilibrium equation of the junction of the rods in the step S2 is as follows:
Figure GDA0002404736840000032
wherein
Figure GDA0002404736840000033
Axial force representing the rod OF;
Figure GDA0002404736840000034
representing the included angle between the direction vector OF the rod OF pointing to F from O and the x axis;
Figure GDA0002404736840000035
represents the axial force of the bar BF;
Figure GDA0002404736840000036
the included angle between the direction vector of the rod BF pointing to F from B and the x axis is represented;
Figure GDA0002404736840000037
represents the axial force of the rod CF;
Figure GDA0002404736840000038
representing the included angle between the direction vector of the rod piece CF pointing to F from C and the x axis;
Figure GDA0002404736840000039
the axial force of the rod piece DF is represented,
Figure GDA00024047368400000310
representing the angle of the direction vector of the rod DF pointing from D to F with the x-axis.
Wherein the moment balance equation of the inner and outer antenna panels in step S2 is:
Figure GDA00024047368400000311
wherein
Figure GDA00024047368400000312
And
Figure GDA00024047368400000313
respectively representing unit direction vectors of the rods after deformation coordination of CF, BF and EF;
Figure GDA00024047368400000314
and
Figure GDA00024047368400000315
a unit direction vector representing the inner and outer antenna panels; k is a radical ofijRepresents the 90 ° locking hinge stiffness coefficient; k is a radical ofojRepresenting the 180 ° locking hinge stiffness coefficient.
Wherein in step S2, the deformation coordination equation is Θ (X) equal to 0; wherein X is ═ lof,lbf,lcf,lef,Δxf,Δyf,θ1,θ2]。
Wherein the basic mathematical model for optimizing and adjusting the rod pieces of the expandable support structure in the step S3 is as follows:
Figure GDA0002404736840000041
wherein U represents the total strain energy of the structure as a whole; k is a radical ofiAnd liRespectively representing the rigidity coefficient and the deformation quantity of the rod piece of the ith rod piece; thetaipRepresenting the geometric accuracy requirements of the inner antenna panel; thetaopRepresenting the accuracy requirement of the outer antenna panel set; thetapThe requirement of the angle difference of the inner antenna panel and the outer antenna panel is shown;
Figure GDA0002404736840000042
a lower limit OF the rod length adjustment amount OF the rod member OF is indicated;
Figure GDA0002404736840000043
the upper limit OF the rod length adjustment amount OF the rod OF is shown.
Compared with the prior art, the invention has the beneficial effects that: the method can be used for quantitatively calculating the deflection angle error, the rod deformation and the rod length adjustment amount of the antenna panel of the satellite-borne planar SAR extensible supporting structure, and provides solid theoretical support for guaranteeing the assembly precision and the unfolding reliability of the satellite-borne planar SAR extensible supporting structure and realizing the accurate quantitative adjustment of the rod length; meanwhile, the basic mathematical model for optimizing and adjusting the rod length is suitable for a satellite-borne planar SAR extensible supporting structure and also suitable for assembling extensible antennas in other aviation fields, and the rod length adjustment amount calculation algorithm adopted in the method is simple and easy to realize and can be selected according to actual requirements.
Further, in both of the rod length adjustment amount calculation methods, since the rod length adjustment amount is a discrete value in actual assembly, the calculation of the rod length adjustment amount is substantially a discrete variable optimization problem. Based on the method, two rod length adjustment calculation algorithms of active search based on discrete variables and rounding based on continuous variables are established from the perspective of the discrete variables and the continuous variables, corresponding algorithms are selected according to actual requirements, rod adjustment is calculated, accurate quantitative adjustment of rods of the extensible support structure is achieved, and assembly accuracy and unfolding reliability are guaranteed.
Furthermore, according to the actual working condition of the expandable support structure, the load bin and the inner and outer antenna panels of the SAR antenna are set as rigid bodies, so that a deformation coordination equation of the expandable support mechanism is conveniently established.
Furthermore, the rod length coordination equation considers the influence of the actual rod length on the rod manufacturing error, the rod length adjustment amount and the rod deformation amount; the force involved in the force balance equation of the junction of the supporting rods is axial tension or pressure generated by deformation of the supporting rods; the torque involved in the torque balance equation of the inner antenna panel and the outer antenna panel comprises the locking hinge reactive torque caused by the axial tension or pressure of the support rod and the deflection angle error of the antenna panel.
Furthermore, a basic mathematical model for optimizing and installing and debugging the rod piece of the expandable support structure is established, and the expansion reliability of the expandable support structure is evaluated by using the integral strain energy of the structure, so that the basic mathematical model for optimizing and installing and debugging the rod piece of the expandable support structure, which can meet the requirement of geometric precision and can ensure that the strain energy of the structure is minimum to realize reliable expansion, is established by taking the total strain energy as an objective function and taking the assembling precision index of the inner and outer antenna panels of the expandable support structure and the adjustment range of the length of the rod piece of the support rod as constraint conditions based on the optimization thought.
Drawings
Fig. 1 is a deployable supporting structure of a spaceborne planar SAR antenna according to the present invention;
FIG. 2 is a schematic view of a deformation of the rod member according to the present invention;
FIG. 3 is a schematic view of the deformation coordination of the deployable support structure of the present invention;
FIG. 4 is a flow chart of an active search assembly adjustment calculation method of the present invention;
fig. 5 is a flowchart of a variable round assembly adjustment amount calculation method according to the present invention.
Detailed Description
The technical solution of the present invention is further explained with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, a plane projection model OF a deployable supporting structure OF a satellite-borne planar SAR antenna is shown, in the actual projection model, a rod member OF, a rod member CF and a rod member EF are actually formed by connecting two rod members through locking hinges, and in order to simplify calculation, the rod members are regarded as an equivalent rod member, and the connection positions OF a and D in fig. 1 are respectively provided with 90-degree and 180-degree locking hinges; as shown in fig. 2, a schematic diagram of the actual length of the rod is given; since the expandable support structure belongs to an overconstrained structure in the assembly process, when the length of the rod is deviated or the hinge installation positioning error exists, the whole structure is subjected to deformation coordination, as shown in fig. 3, a solid line represents an ideal configuration, and a dotted line represents an actual configuration after the deformation coordination.
The invention provides a method for adjusting and installing a rod piece of an expandable support structure of a satellite-borne planar SAR antenna, which takes the rod piece of the expandable support structure of four support rod pieces shown in figures 1 and 3 as an example, and comprises the following steps:
step S1, determining the geometric parameters of the deployable supporting mechanism, setting the load bin and the inner and outer antenna panels of the SAR antenna as rigid bodies, determining the rigidity parameters of the locking hinge, and determining the material parameters of the rod piece;
step S2, a rod length coordination equation is established, as shown in fig. 2, the actual support rod is affected by the manufacturing error, the adjustment amount and the deformation, so the actual length of the rod is lC＝l0+ Δ l + l (1) where lCRepresenting the actual length of the individual bars after deformation coordination, l0Indicating the designed length of the rod; l is the deformation of the rod; delta l is the rod error; wherein the rod error Δ l ═ Δ la+Δlm(2) Wherein Δ laAnd Δ lmThe rod length adjustment values and rod length manufacturing tolerances are expressed separately, so for the four support rods shown in fig. 1 and 3, the coordination equation is:
Figure GDA0002404736840000061
wherein O, D, C, B represent the actual coordinates of the end points of the expandable support structure after the coordination of the deformation, F represents the reference coordinate point [ Delta x ]f,Δyf]；lofThe design length for the rod OF; Δ lofIs the rod length deviation OF the rod OF; lofIs the amount OF deformation OF the rod OF; ldfDesigning the length of the rod piece DF; Δ ldfThe rod length deviation of the rod piece DF; ldfThe deformation of the rod piece DF; lcfThe design length for the rod CF; Δ lcfThe rod length deviation of the rod member CF; lcfThe deformation amount of the rod member CF; lbfDesigning the length of the rod BF; Δ lbfThe length deviation of the bar BF; lbfThe amount of deformation of the bar BF.
Establishing a mechanical balance equation of the member bar intersection points, wherein the four acting forces are received by the four supporting rod acting intersection points F, which are respectively lbf、lcf、lofAnd lefThe acting force is decomposed into two directions of an x axis and a y axis, and the obtained mechanical balance equation is as follows:
Figure GDA0002404736840000071
wherein
Figure GDA0002404736840000072
Axial force representing the rod OF;
Figure GDA0002404736840000073
representing the included angle between the direction vector OF the rod OF pointing to F from O and the x axis;
Figure GDA0002404736840000074
represents the axial force of the bar BF;
Figure GDA0002404736840000075
the included angle between the direction vector of the rod BF pointing to F from B and the x axis is represented;
Figure GDA0002404736840000076
represents the axial force of the rod CF;
Figure GDA0002404736840000077
representing the included angle between the direction vector of the rod piece CF pointing to F from C and the x axis;
Figure GDA0002404736840000078
the axial force of the rod piece DF is represented,
Figure GDA0002404736840000079
representing the angle of the direction vector of the rod DF pointing from D to F with the x-axis.
Establishing a moment balance equation of the inner antenna panel and the outer antenna panel, wherein for the inner antenna panel AD, the moment generated by the axial force of the rod BF and the CF is received, and the counter-resisting moments of the 90-degree and 180-degree locking hinges are also received; for the outer antenna panel DE, the moment generated by the axial force of the rod EF, and the counter moment of the 180 ° locking hinge, the moment balance equation for the inner and outer antenna panels is:
Figure GDA00024047368400000710
wherein
Figure GDA00024047368400000711
And
Figure GDA00024047368400000712
respectively representing unit direction vectors of the rods after deformation coordination of CF, BF and EF;
Figure GDA00024047368400000713
and
Figure GDA00024047368400000714
a unit direction vector representing the inner and outer antenna panels; k is a radical ofijRepresents the 90 ° locking hinge stiffness coefficient; k is a radical ofojRepresenting the 180 ° locking hinge stiffness coefficient.
The above equations (3), (4) and (5) jointly form the condition for coordinating the deformation of the expandable support structure, so that the deformation coordination equation is obtained as Θ (X) being 0; wherein X is ═ lof,lbf,lcf,lef,Δxf,Δyf,θ1,θ2]。
Step S3, establishing an optimal adjustment basic mathematical model of the expandable support structure rod piece; the smaller the total strain energy of the expandable support structure is, the smaller the 'holding force' in the structure is, and the smoother and more reliable the expansion and locking of the expandable support structure are. Therefore, by taking the total strain capacity as an objective function, and taking the rod length coordination equation, the rod intersection point mechanical balance equation, the internal and external antenna panel moment balance equation and the support rod length adjustment range as constraint conditions, the basic mathematical model for optimal adjustment of the rods of the expandable support structure is obtained as follows:
Figure GDA0002404736840000081
wherein U represents the total strain energy of the structure as a whole; k is a radical ofiAnd liRespectively representing the rigidity coefficient and the deformation quantity of the rod piece of the ith rod piece; thetaipRepresenting the geometric accuracy requirements of the inner antenna panel; thetaopRepresenting the accuracy requirement of the outer antenna panel set; thetapThe requirement of the angle difference of the inner antenna panel and the outer antenna panel is shown;
Figure GDA0002404736840000082
a lower limit OF the rod length adjustment amount OF the rod member OF is indicated;
Figure GDA0002404736840000083
the upper limit OF the rod length adjustment amount OF the rod OF is shown.
And step S4, calculating the rod length adjustment amount through the basic mathematical model obtained in the step S3 to obtain the optimal rod length adjustment amount combination, and finishing accurate adjustment. In actual engineering, since the rod length adjustment amount is a discrete variable, when calculating the rod length adjustment amount using the basic mathematical model in step S3, it is necessary to establish an active search based on discrete variable consideration or a variable rounding two rod length adjustment amount calculation processes based on continuous variable consideration.
As shown in fig. 4, the active search method based on discrete variables specifically includes the following steps: firstly, determining a high-yield adjustment range and adjustment intervals, and generating all rod length adjustment combinations based on an exhaustion method; then, combining all the rod length adjustment quantities into a formula (6), and calculating the total strain energy and the angle deviation of the inner antenna panel and the outer antenna panel; and then, sorting the total strain energy corresponding to the strain energy which meets the requirement of the precision index from the screening position, thereby finding the optimal rod length adjustment amount combination which meets the requirement of the minimum total strain energy and the assembly precision requirement, and then finishing the precise adjustment.
As shown in fig. 5, the specific process of the variable rounding method based on the continuous variable is as follows: giving an initial value of X in the formula (6) and upper and lower limit values of the adjustment amount, and directly calculating to obtain an optimal adjustment combination based on an optimization algorithm; the optimum adjustment is then rounded to a practical adjustable value (including round up and round down), which can be combined into 16 new rod length adjustment combinations (4 rods, 2 total)4Seed combinations); the rounded 16 middle rod length adjustment amount combination is substituted into a formula (6), and the total strain energy and the angle deviation of the inner antenna panel and the outer antenna panel are calculated; and (4) sorting the total strain energy corresponding to the strain energy meeting the requirement of the precision index from the screening part, so as to find the optimal rod length adjustment amount combination meeting the minimum total strain energy and meeting the requirement of assembly precision, and then finishing accurate adjustment.
Step S4 of the present invention provides two methods for calculating the optimal combination of rod length adjustments, and one of them may be selected according to the actual requirements of the operating conditions.

Claims (6)

1. A method for adjusting and installing a rod piece of a deployable supporting structure of a satellite-borne planar SAR antenna is characterized by comprising the following steps:
step S1, determining geometric parameters of the expandable support structure and rigidity parameters of the locking hinge;
step S2, establishing a deformation coordination equation of the expandable support structure, wherein the deformation coordination equation comprises a rod length coordination equation, a rod intersection point mechanical equilibrium equation and an inner and outer antenna panel moment equilibrium equation;
the rod length coordination equation is:
Figure FDA0002416353710000011
wherein O, D, C, B represent the actual coordinates of the end points of the expandable support structure after the coordination of the deformation, F represents the reference coordinate point [ Delta x ]f,Δyf]；lofThe design length for the rod OF; Δ lofIs the rod length deviation OF the rod OF; lofIs the amount OF deformation OF the rod OF; ldfDesigning the length of the rod piece DF; Δ ldfThe rod length deviation of the rod piece DF; ldfThe deformation of the rod piece DF; lcfThe design length for the rod CF; Δ lcfThe rod length deviation of the rod member CF; lcfThe deformation amount of the rod member CF; lbfDesigning the length of the rod BF; Δ lbfThe length deviation of the bar BF; lbfThe deformation of the bar BF;
the rod member intersection point mechanical balance equation is as follows:
Figure FDA0002416353710000012
wherein
Figure FDA0002416353710000014
Axial force representing the rod OF;
Figure FDA0002416353710000015
representing the included angle between the direction vector OF the rod OF pointing to F from O and the x axis;
Figure FDA0002416353710000016
represents the axial force of the bar BF;
Figure FDA0002416353710000017
the included angle between the direction vector of the rod BF pointing to F from B and the x axis is represented;
Figure FDA0002416353710000018
represents the axial force of the rod CF;
Figure FDA0002416353710000019
representing the included angle between the direction vector of the rod piece CF pointing to F from C and the x axis;
Figure FDA00024163537100000110
the axial force of the rod piece DF is represented,
Figure FDA00024163537100000111
representing the included angle between the direction vector of the rod piece DF pointing to F from D and the x axis;
the moment balance equation of the inner and outer antenna panels is as follows:
Figure FDA0002416353710000013
wherein
Figure FDA00024163537100000112
And
Figure FDA00024163537100000113
respectively representing unit direction vectors of the rods after deformation coordination of CF, BF and EF;
Figure FDA0002416353710000021
and
Figure FDA0002416353710000022
a unit direction vector representing the inner and outer antenna panels; k is a radical ofijRepresents the 90 ° locking hinge stiffness coefficient; k is a radical ofojRepresents the 180 ° locking hinge stiffness coefficient;
step S3, establishing an optimized adjustment basic mathematical model of the expandable support structure rod piece by taking the total deformation energy of the SAR antenna as a target function and the deformation coordination equation in the step S2 as a constraint condition;
and step S4, calculating the rod length adjustment quantity through the basic mathematical model in the step S3 to obtain the optimal rod length adjustment quantity combination, and finishing accurate adjustment.
2. The method for adjusting rods of the deployable support structure of a spaceborne planar SAR antenna as claimed in claim 1, wherein the method for calculating the rod length adjustment amount in the step S4 is an active search method starting from discrete variables or a variable rounding method starting from continuous variables.
3. The method for adjusting and installing the rods of the deployable support structure of the spaceborne planar SAR antenna, according to claim 2, is characterized in that the specific process of the active search method starting from the discrete variables is as follows: generating all rod length adjustment amount combinations according to the rod length adjustment amount range and the adjustment amount interval; then substituting the rod length adjustment combination into a basic mathematical model to calculate to obtain total strain energy and the angle deviation of the inner antenna panel and the outer antenna panel; and selecting a plurality of rod length adjustment amount combinations meeting the index requirements, and sequencing according to the total strain energy of the rod length adjustment amount combinations to obtain the optimal rod length adjustment amount combination with the minimum total strain energy.
4. The method for adjusting and installing the rods of the deployable supporting structure of the spaceborne planar SAR antenna as claimed in claim 1, wherein the loading bin and the inner and outer antenna panels of the SAR antenna are set as rigid bodies in the step S1.
5. The method for adjusting the rods of the deployable supporting structure of the spaceborne planar SAR antenna according to any one of claims 1, wherein in the step S2, the deformation coordination equation is Θ (X) ═ 0; wherein
X＝[lof,lbf,lcf,lef,Δxf,Δyf,θ1,θ2]。
6. The method for adjusting the rods of the deployable support structure of the spaceborne planar SAR antenna according to claim 5, wherein the basic mathematical model for optimizing and adjusting the rods of the deployable support structure in the step S3 is as follows:
Figure FDA0002416353710000031
wherein U represents the total strain energy of the structure as a whole; k is a radical ofiAnd liRespectively representing the rigidity coefficient and the deformation quantity of the rod piece of the ith rod piece; thetaipRepresenting the geometric accuracy requirements of the inner antenna panel; thetaopRepresenting the accuracy requirement of the outer antenna panel set; thetapThe requirement of the angle difference of the inner antenna panel and the outer antenna panel is shown;
Figure FDA0002416353710000032
a lower limit OF the rod length adjustment amount OF the rod member OF is indicated;
Figure FDA0002416353710000033
the upper limit OF the rod length adjustment amount OF the rod OF is shown.
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