CN108363884A - A kind of spaceborne plane SAR antennas can open up support construction rod piece tune dress method - Google Patents
A kind of spaceborne plane SAR antennas can open up support construction rod piece tune dress method Download PDFInfo
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Abstract
Support construction rod piece tune can be opened up the invention discloses a kind of spaceborne plane SAR antennas and fills method, included the following steps：Determination can open up the geometric parameter and locking hinge stiffness parameters of support construction；The Coordinate deformation equation of support construction can be opened up by establishing, and Coordinate deformation equation includes the long equation of comptability of bar, rod piece joint mechanical balance equation and inside and outside aerial panel torque equilibrium equation；Can be object function with the total deformation of SAR antennas, using three equations in step S2 as constraints, foundation can open up the optimization of support construction rod piece and adjust dress basic mathematic model；Adjusting bar-length amount is calculated by the basic mathematic model in step S3, completes accurate adjustment.This method is with the minimum object function of structural strain energy, precisely the accurate quantitative digital of support construction rod piece can be opened up for the spaceborne plane SAR antennas of constraints with assembly with Coordinate deformation equation and optimize integration techno logy, realize the method that rod piece is adjusted in quantitative digital makeup during ground-mounted.
Description
Technical field
The invention belongs to spaceborne plane SAR antenna tune to fill technical field；It can be opened up more particularly to a kind of spaceborne plane SAR antennas
Support construction rod piece tune fills method.
Background technology
Spaceborne plane SAR satellite antennas can open up that the constraint of support construction ring is more, and topological structure is complicated, belong to typically polycyclic and close
Chain member structure.In order to realize spaceborne plane SAR satellite antennas in space smoothly expansion and normal service, it is necessary on ground
Ensure that support construction assembly precision can be opened up in the assembling process of face.But due to by rod length error, hinge assemblies position error with
Deformation Member influences, and satellite antenna pointing accuracy often exceeds design requirement.For this purpose, engineering staff generally requires in ground-mounted
Adjusting bar-length is carried out to supporting bar in the process.However at present in aerospace enterprise group using measurement --- adjustment --- measurement
Pure experience " blind tune " pattern, not only assembly period is long, time and effort consuming, and often can not meet can open up support construction assembly essence
Degree and the requirement being reliably unfolded.Thus spaceborne plane SAR satellite antennas, which may be implemented, in one kind can open up support construction rod piece precisely calmly
The method of adjustment is measured for shortening the adjustment period, it is most important to improve expansion reliability.
Domestic technology and document about this respect is fewer and fewer at present, can be used for open up without ripe or ready-made method
Support construction rod piece adjustment amount calculates.It is proposed that one kind being suitable for spaceborne plane SAR satellite antennas and can open up support construction rod piece thus
Quantitative optimization Method of Adjustment, to solve the work by adjustment excessive cycle and " Zhan Bukai " and " can't lock " caused by " blind tune "
Journey persistent ailment.
Invention content
Support construction rod piece tune, which can be opened up, the present invention provides a kind of spaceborne plane SAR antennas fills method；With structural strain energy
Minimum object function precisely can open up support knot with Coordinate deformation equation and assembly for the spaceborne plane SAR antennas of constraints
The accurate quantitative digital of structure rod piece optimizes integration techno logy, realizes the method that rod piece is adjusted in quantitative digital makeup during ground-mounted.
The technical scheme is that：A kind of spaceborne plane SAR antennas can open up support construction rod piece tune dress method, including with
Lower step：
Step S1, determination can open up the geometric parameter and locking hinge stiffness parameters of support construction；
Step S2 establishes the Coordinate deformation equation that can open up support construction, and Coordinate deformation equation includes the long equation of comptability of bar, bar
Part joint mechanical balance equation and inside and outside aerial panel torque equilibrium equation；
Step S3 can be object function with the total deformation of SAR antennas, be constraint item with the Coordinate deformation equation in step S2
Part, foundation can open up the optimization of support construction rod piece and adjust dress basic mathematic model；
Step S4 calculates adjusting bar-length amount by the basic mathematic model in step S3, obtains optimal adjusting bar-length amount group
It closes, completes accurate adjustment.
Further, the features of the present invention also characterized in that：
The method that adjusting bar-length amount is calculated in wherein step S4 is from the active searching method of discrete variable or from even
The variable rounding method that continuous variable sets out.
Wherein it is from the detailed process of the active searching method of discrete variable：According to adjusting bar-length amount range and adjustment
Amount interval generates all adjusting bar-length amount combinations；Then the combination of above-mentioned adjusting bar-length amount is brought into basic mathematic model and is calculated
To total strain energy and inside and outside aerial panel angular deviation；Selection meets multiple adjusting bar-length amounts combination of index request, and root
It is ranked up according to its total strain energy, obtains the optimal adjusting bar-length amount combination of total strain energy minimum.
Wherein it is from the detailed process of the variable rounding method of continuous variable：Optimal correction is settled accounts based on optimization algorithm
Amount combination；Then optimal correction amount is combined into rounding to practical adjustable numerical value, and obtains multiple new adjusting bar-length amount combinations；
The combination of multiple adjusting bar-length amounts is brought into basic mathematic model, total strain energy and inside and outside aerial panel angular deviation is calculated；
Selection meets multiple adjusting bar-length amounts combination of index request, and is ranked up according to its total strain energy, obtains total strain energy
Minimum optimal adjusting bar-length amount combination.
It sets the load storehouse of SAR antennas and inside and outside aerial panel to rigid body in wherein step S1.
The long equation of comptability of bar is in wherein step S2：Wherein O*, D*, C*, B* table
Show that the actual coordinate that can open up support construction endpoint after compatibility of deformation, F* indicate reference coordinate point [Δ xf,Δyf]；lofFor bar
The design length of part OF；ΔlofFor the long deviation of bar of rod piece OF；δlofFor the deflection of rod piece OF；lofDesign for rod piece OF is grown
Degree；ΔlofFor the long deviation of bar of rod piece OF；δlofFor the deflection of rod piece OF；ldfFor the design length of rod piece DF；ΔldfFor bar
The long deviation of bar of part DF；δldfFor the deflection of rod piece DF；lcfFor the design length of rod piece CF；ΔlcfIt is inclined for the bar length of rod piece CF
Difference；δlcfFor the deflection of rod piece CF；lbfFor the design length of rod piece BF；ΔlbfFor the long deviation of bar of rod piece BF；δlbfFor rod piece
The deflection of BF.
Rod piece joint mechanical balance equation is in wherein step S2：Wherein
fo*f*Indicate the axial force of rod piece OF；θo*f*Indicate that rod piece OF is directed toward the angle of the direction vector and x-axis of F by O；fb*f*Indication rod
The axial force of part BF；θb*f*Indicate that rod piece BF is directed toward the angle of the direction vector and x-axis of F by B；fc*f*Indicate the axial direction of rod piece CF
Power；θc*f*Indicate that rod piece CF is directed toward the angle of the direction vector and x-axis of F by C；fd*f*Indicate the axial force of rod piece DF, θd*f*It indicates
Rod piece DF is directed toward the angle of the direction vector and x-axis of F by D.
Inside and outside aerial panel torque equilibrium equation is in wherein step S2：Its
Middle nc*f*、nb*f*And ne*f*The unit direction vector after rod piece CF, BF and EF compatibility of deformation is indicated respectively；nac*And nd*e*In expression
The unit direction vector of outside antenna panel；kijIndicate 90 ° of locking hinge stiffness coefficients；kojIndicate 180 ° of locking hinge rigidity systems
Number.
Coordinate deformation equation is Θ (X)=0 in wherein step S2；Wherein X=[δ lof,δlbf,δlcf,δlef,Δxf,Δ
yf,θ1,θ2]。
Support construction rod piece optimization tune dress basic mathematic model can be opened up in wherein step S3 is：
Wherein U indicates structure entirety total strain energy；kiWith δ liThe stiffness coefficient and rod piece deformation quantity of i-th of rod piece are indicated respectively；θipTable
Show the requirement of internal antenna panel geometric accuracy；θopIndicate outside antenna panel set required precision；θpIndicate inside and outside aerial panel angle
Difference requires；Indicate the adjusting bar-length amount lower limit of rod piece OF；Indicate the adjusting bar-length amount lower limit of rod piece OF.
Compared with prior art, the beneficial effects of the invention are as follows：This method, which can carry out spaceborne plane SAR, can open up support knot
Structure aerial panel deflection angle error, Deformation Member, the long adjustment amount of bar quantitatively calculate, to ensure that spaceborne plane SAR can open up support
Standard precision and expansion reliability, realize that bar grows accurate quantitative adjusting and provides solid theory support；This method simultaneously
The bar length of offer, which optimizes and revises basic mathematic model and is applicable not only to spaceborne plane SAR, can open up support construction, for other aviations
The Deployable antenna assembly in field is equally applicable, and the adjusting bar-length amount computational algorithm used in this method in addition is simple, it is easy to accomplish,
It can be selected for actual demand.
Further, in two kinds of adjusting bar-length amount computational methods, in view of in being practical set, adjusting bar-length amount be from
Value is dissipated, therefore the calculating of adjusting bar-length amount is substantially Discrete Variables Optimization.Based on this, from discrete variable and continuous variable two
A angle is set out, and is established the active search based on discrete variable and is calculated with based on the two kinds of adjusting bar-length amounts calculating of continuous variable rounding
Method, and corresponding algorithm is selected according to actual demand, rod piece adjustment amount is calculated, it is precisely quantitative that realization can open up support construction rod piece
Adjustment ensures assembly precision and expansion reliability.
Further, according to the actual condition that can open up support construction, by the load storehouse of SAR antennas and inside and outside aerial panel
It is set as rigid body, facilitates foundation that can open up supporting mechanism Coordinate deformation equation.
Further, the long equation of comptability of bar is grown in view of practical bar receives rod piece foozle, adjusting bar-length amount and bar
The influence of part deflection；Involved power is supporting rod due to axis caused by deformation in supporting rod joint equilibrium equation
To pulling force or pressure；Involved in inside and outside aerial panel torque equilibrium equation to torque include supporting rod axial tension or pressure
There is caused locking hinge resistance torque after deflection angle error in torque and the aerial panel that power generates.
Further, foundation can open up support construction rod piece optimization adjustment basic mathematic model, integrally be strained using structure
Support construction expansion reliability can be opened up to evaluate, to be based on optimization thought, using total strain energy as object function, and more than
That states foundation opens up support construction Coordinate deformation equation, can open up aerial panel assembly precision index and support inside and outside support construction
Bar adjusting bar-length amount ranging from constraints, foundation can meet geometric accuracy require and structural strain can it is minimum with
Realize that is reliably unfolded opens up support construction rod piece optimization adjustment basic mathematic model.
Description of the drawings
Fig. 1 is that spaceborne plane SAR antennas can open up support construction in the present invention；
Fig. 2 is the schematic diagram of Deformation Member in the present invention；
Fig. 3 is that can open up support construction compatibility of deformation schematic diagram in the present invention；
Fig. 4 is the flow chart that equipment adjustment amount computational methods are actively searched in the present invention；
Fig. 5 is the flow chart of variable rounding equipment adjustment amount computational methods in the present invention.
Specific implementation mode
Technical scheme of the present invention is further illustrated in the following with reference to the drawings and specific embodiments.
As shown in Figure 1, support construction plane projection model can be opened up for spaceborne plane SAR antennas, in practical projection model,
Rod piece OF, CF are really connected by locking hinge by two rod pieces with EF and are formed, and are calculated to simplify, are regarded as one etc.
Rod piece is imitated, A is respectively arranged with 90 ° and 180 ° of locking hinges with the junctions D in Fig. 1；As shown in Fig. 2, giving rod piece actual (tube) length
Spend schematic diagram；Belong to Planar Mechanisms structure in assembling process since support construction can be opened up, when deviation or hinge peace occurs in bar length
In the presence of filling position error, total can carry out compatibility of deformation, as shown in figure 3, solid line indicates that ideal configuration, dotted line indicate to become
Actual configuration after shape coordination.
Support construction rod piece tune can be opened up the present invention provides a kind of spaceborne plane SAR antennas and fills method, and the present embodiment is with such as
Opening up for four supporting bars shown in Fig. 1 and 3 is said for support construction rod piece comprising following steps：
Step S1, determination can open up the geometric parameter of supporting mechanism, and by the load storehouse of SAR antennas and inside and outside aerial panel
It is set as rigid body, while determining locking hinge stiffness parameters, further includes determining bar material parameter；
Step S2 establishes the long equation of comptability of bar, as shown in Fig. 2, actual support bar receives foozle, adjustment amount and change
The influence of shape, therefore the physical length of rod piece is lC=l0+Δl+δl (1)
Wherein lCIndicate the physical length after single Deformation Member is coordinated, l0Indicate the design length of rod piece；δ l are Deformation Member
Amount；Δ l is rod piece error；Wherein rod piece error delta l=Δs la+Δlm (2)
Wherein Δ laWith Δ lmThe long adjusted value of indication rod and the long foozle of bar respectively, therefore for as shown in figs. 1 and 3 four
For supporting bar, the equation of comptability is：
Wherein O*, D*, C*, B* expression can open up actual coordinate of the support construction endpoint after compatibility of deformation, and F* indicates that benchmark is sat
Punctuate [Δ xf,Δyf]；lofFor the design length of rod piece OF；ΔlofFor the long deviation of bar of rod piece OF；δlofFor the deformation of rod piece OF
Amount；lofFor the design length of rod piece OF；ΔlofFor the long deviation of bar of rod piece OF；δlofFor the deflection of rod piece OF；ldfFor rod piece
The design length of DF；ΔldfFor the long deviation of bar of rod piece DF；δldfFor the deflection of rod piece DF；lcfDesign for rod piece CF is grown
Degree；ΔlcfFor the long deviation of bar of rod piece CF；δlcfFor the deflection of rod piece CF；lbfFor the design length of rod piece BF；ΔlbfFor bar
The long deviation of bar of part BF；δlbfFor the deflection of rod piece BF.
Rod piece joint mechanical balance equation is established, work receives four active forces at four supporting rod effect joint F*,
It is respectively lbf、lcf、lofAnd lefAxial drawing/pressure obtain its power by its Force decomposition to x and y-axis both direction
Learning equilibrium equation is：
Wherein fo*f*Indicate the axial force of rod piece OF；θo*f*Indicate that rod piece OF is directed toward the angle of the direction vector and x-axis of F by O；
fb*f*Indicate the axial force of rod piece BF；θb*f*Indicate that rod piece BF is directed toward the angle of the direction vector and x-axis of F by B；fc*f*Indication rod
The axial force of part CF；θc*f*Indicate that rod piece CF is directed toward the angle of the direction vector and x-axis of F by C；fd*f*Indicate the axial direction of rod piece DF
Power, θd*f*Indicate that rod piece DF is directed toward the angle of the direction vector and x-axis of F by D.
It establishes inside and outside aerial panel torque equilibrium equation and rod piece BF and CF axial forces is received for internal antenna panel AD
Generated torque, the resistance torque of also 90 ° and 180 ° locking hinges；For outside antenna panel DE, by rod piece EF axis
To torque caused by power and the resistance torque of 180 ° of locking hinges, therefore inside and outside aerial panel torque equilibrium equation is：
Wherein nc*f*、nb*f*And ne*f*The unit direction vector after rod piece CF, BF and EF compatibility of deformation is indicated respectively；nac*With
nd*e*Indicate the unit direction vector of inside and outside aerial panel；kijIndicate 90 ° of locking hinge stiffness coefficients；kojIndicate 180 ° of locking hinges
Chain stiffness coefficient.
Above formula (3), (4) and (5) has collectively constituted the condition that can open up support construction compatibility of deformation, therefore is deformed
The equation of comptability is Θ (X)=0；Wherein X=[δ lof,δlbf,δlcf,δlef,Δxf,Δyf,θ1,θ2]。
Step S3, foundation can open up the optimization of support construction rod piece and adjust dress basic mathematic model；Support construction total strain energy can be opened up
Smaller, inside configuration " suppressing strength " is smaller, and expansion locking is more smooth reliable.Therefore, using overall strain ability as object function, with
The long equation of comptability of above-mentioned bar, rod piece joint mechanical balance equation and inside and outside aerial panel torque equilibrium equation and supporting rod
Adjusting bar-length amount ranging from constraints, support construction rod piece optimization adjustment basic mathematic model can be opened up by, which obtaining, is：
Wherein U indicates structure entirety total strain energy；kiWith δ liStiffness coefficient and the rod piece deformation of i-th of rod piece are indicated respectively
Amount；θipIndicate the requirement of internal antenna panel geometric accuracy；θopIndicate outside antenna panel set required precision；θpIndicate inside and outside antenna surface
The requirement of plate differential seat angle；Indicate the adjusting bar-length amount lower limit of rod piece OF；Under the adjusting bar-length amount for indicating rod piece OF
Limit.
Step S4 calculates adjusting bar-length amount by the basic mathematic model obtained in step S3, obtains optimal adjusting bar-length
Amount combination, completes accurate adjustment.In Practical Project, adjusting bar-length amount is discrete variable, therefore is utilized basic in step S3
When mathematical model calculates adjusting bar-length amount, need to establish the active search considered based on discrete variable or based on continuous variable consideration
Two kinds of adjusting bar-length amount calculating process of variable rounding.
As shown in figure 4, the detailed process of the active searching method to be set out based on discrete variable is：High yield adjustment is determined first
Range and adjustment amount interval are measured, and all adjusting bar-length amount combinations are generated based on the method for exhaustion；Then above-mentioned all bars are long
Adjustment amount combination is brought into formula (6), and total strain energy and inside and outside aerial panel angular deviation are calculated；Then full from wherein screening place
What sufficient precision index required, and the total strain energy corresponding to it is ranked up, meet total strain energy minimum to find, and
Then the optimal adjusting bar-length amount combination for reaching assembly precision requirement is completed precisely to adjust dress.
As shown in figure 5, the detailed process for the variable rounding method set out based on continuous variable is：Provide X in formula (6)
The upper lower limit value of initial value and adjustment amount, and optimal correction combination is directly calculated based on optimization algorithm；It then will most
For excellent adjustment amount rounding to practical adjustable value (including upward rounding and downward rounding), above-mentioned rounding value can make up 16 kinds of new bars
The combination of long adjustment amount (4 bars, totally 24Kind combination)；By rounding come out 16 in adjusting bar-length amount combination bring into formula (6), count
Calculate total strain energy and inside and outside aerial panel angular deviation；Meet precision index requirement from wherein screening place, and right to its institute
The total strain energy answered is ranked up, and meets total strain energy minimum to find, and the optimal bar length for reaching assembly precision requirement is adjusted
Then whole amount combination is completed precisely to adjust dress.
Step S4 gives two kinds of methods for calculating optimal adjusting bar-length amount combination in the present invention, according to the practical need of operating mode
It wants, selects one of which.
Claims (10)
1. a kind of spaceborne plane SAR antennas can open up support construction rod piece tune dress method, which is characterized in that include the following steps：
Step S1, determination can open up the geometric parameter and locking hinge stiffness parameters of support construction；
Step S2, establishes the Coordinate deformation equation that can open up support construction, and Coordinate deformation equation includes the long equation of comptability of bar, rod piece friendship
Meeting point mechanical balance equation and inside and outside aerial panel torque equilibrium equation；
Step S3 can be object function with the total deformation of SAR antennas, using the Coordinate deformation equation in step S2 as constraints, build
It is vertical to open up support construction rod piece optimization tune dress basic mathematic model；
Step S4 calculates adjusting bar-length amount by the basic mathematic model in step S3, obtains optimal adjusting bar-length amount combination, complete
At accurate adjustment.
2. spaceborne plane SAR antennas according to claim 1 can open up support construction rod piece tune dress method, which is characterized in that
The method that adjusting bar-length amount is calculated in the step S4 is to go out from the active searching method of discrete variable or from continuous variable
The variable rounding method of hair.
3. spaceborne plane SAR antennas according to claim 2 can open up support construction rod piece tune dress method, which is characterized in that
The detailed process of the active searching method from discrete variable is：It is given birth to according to adjusting bar-length amount range and adjustment amount interval
It is combined at all adjusting bar-length amounts；Then the combination of above-mentioned adjusting bar-length amount is brought into and overall strain is calculated in basic mathematic model
It can be with inside and outside aerial panel angular deviation；Selection meets multiple adjusting bar-length amounts combination of index request, and is always answered according to it
Change can be ranked up, and obtain the optimal adjusting bar-length amount combination of total strain energy minimum.
4. spaceborne plane SAR antennas according to claim 2 can open up support construction rod piece tune dress method, which is characterized in that
The detailed process of the variable rounding method from continuous variable is：Based on optimization algorithm clearing optimal correction amount combination；
Then optimal correction amount is combined into rounding to practical adjustable numerical value, and obtains multiple new adjusting bar-length amount combinations；It will be multiple
The combination of adjusting bar-length amount, which is brought into basic mathematic model, is calculated total strain energy and inside and outside aerial panel angular deviation；Selection is full
Multiple adjusting bar-length amounts of sufficient index request combine, and are ranked up according to its total strain energy, obtain total strain energy minimum
Optimal adjusting bar-length amount combination.
5. spaceborne plane SAR antennas according to claim 1 can open up support construction rod piece tune dress method, which is characterized in that
It sets the load storehouse of SAR antennas and inside and outside aerial panel to rigid body in the step S1.
6. spaceborne plane SAR antennas according to claim 1 can open up support construction rod piece tune dress method, which is characterized in that
The long equation of comptability of bar is in the step S2：Wherein O*, D*, C*, B* expression can open up branch
Actual coordinate of the support structure endpoint after compatibility of deformation, F* indicate reference coordinate point [Δ xf,Δyf]；lofFor setting for rod piece OF
Count length；ΔlofFor the long deviation of bar of rod piece OF；δlofFor the deflection of rod piece OF；lofFor the design length of rod piece OF；Δlof
For the long deviation of bar of rod piece OF；δlofFor the deflection of rod piece OF；ldfFor the design length of rod piece DF；ΔldfFor the bar of rod piece DF
Long deviation；δldfFor the deflection of rod piece DF；lcfFor the design length of rod piece CF；ΔlcfFor the long deviation of bar of rod piece CF；δlcfFor
The deflection of rod piece CF；lbfFor the design length of rod piece BF；ΔlbfFor the long deviation of bar of rod piece BF；δlbfFor the deformation of rod piece BF
Amount.
7. spaceborne plane SAR antennas according to claim 1 can open up support construction rod piece tune dress method, which is characterized in that
Rod piece joint mechanical balance equation is in the step S2：
Wherein fo*f*It indicates
The axial force of rod piece OF；θo*f*Indicate that rod piece OF is directed toward the angle of the direction vector and x-axis of F by O；fb*f*Indicate the axis of rod piece BF
Xiang Li；θb*f*Indicate that rod piece BF is directed toward the angle of the direction vector and x-axis of F by B；fc*f*Indicate the axial force of rod piece CF；θc*f*Table
Show that rod piece CF is directed toward the angle of the direction vector and x-axis of F by C；fd*f*Indicate the axial force of rod piece DF, θd*f*Indicate rod piece DF by D
It is directed toward the angle of the direction vector and x-axis of F.
8. spaceborne plane SAR antennas according to claim 1 can open up support construction rod piece tune dress method, which is characterized in that
Inside and outside aerial panel torque equilibrium equation is in the step S2：
Wherein nc*f*、nb*f*And ne*f*Table respectively
Show the unit direction vector after rod piece CF, BF and EF compatibility of deformation；nac*And nd*e*Indicate the unit direction of inside and outside aerial panel to
Amount；kijIndicate 90 ° of locking hinge stiffness coefficients；kojIndicate 180 ° of locking hinge stiffness coefficients.
9. the spaceborne plane SAR antennas according to claim 6-8 any one can open up support construction rod piece tune dress method,
It is characterized in that, Coordinate deformation equation is Θ (X)=0 in the step S2；Wherein
X=[δ lof,δlbf,δlcf,δlef,Δxf,Δyf,θ1,θ2]。
10. spaceborne plane SAR antennas according to claim 9 can open up support construction rod piece tune dress method, which is characterized in that
Support construction rod piece optimization tune dress basic mathematic model can be opened up in the step S3 is：
Wherein U indicates structure entirety total strain energy；kiWith δ liThe stiffness coefficient and rod piece deformation quantity of i-th of rod piece are indicated respectively；
θipIndicate the requirement of internal antenna panel geometric accuracy；θopIndicate outside antenna panel set required precision；θpIndicate inside and outside aerial panel
Differential seat angle requirement；Indicate the adjusting bar-length amount lower limit of rod piece OF；Indicate the adjusting bar-length amount lower limit of rod piece OF.
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| CN109190282A (en) * | 2018-09-19 | 2019-01-11 | 西安交通大学 | A kind of the equipment adjustment method and its control device, mechanical device of closed chain mechanism |
| CN109800505A (en) * | 2019-01-21 | 2019-05-24 | 西安交通大学 | A kind of borne SAR space can open up support construction assembly precision prediction technique |
| CN111883937A (en) * | 2020-07-20 | 2020-11-03 | 上海宇航系统工程研究所 | Rapid and accurate adjustment method for attitude precision of multi-plate planar antenna array surface |
| CN113219426A (en) * | 2021-05-21 | 2021-08-06 | 上海航天电子通讯设备研究所 | Large-size SAR antenna assembly measurement method |
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