CN104850697B - Large-scale antenna dynamic modeling method based on ANSYS and ADAMS - Google Patents
Large-scale antenna dynamic modeling method based on ANSYS and ADAMS Download PDFInfo
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Abstract
The problem of the invention discloses a kind of large-scale antenna dynamic modeling method based on ANSYS and ADAMS, mainly solving the rigid motion that existing modeling method is unable to accurate description antenna, and can not considering the Rigid-elastic Coupling during antenna movement, implementation step is：Based on the FEM model of the elastic component of large-scale reflector antenna, according to its modal analysis result, the selection mode big to antenna output variable contribution degree, node coordinate is replaced to carry out polycondensation to the free degree of elastic deformation using a small amount of modal coordinate, then modal neutral file corresponding to export；By establishing the rigid body component of antenna in ADAMS, with reference to the modal neutral file of description elastomer, the Dynamics Simulation Model of antenna mass motion can must be described by carrying out assembling.Instant invention overcomes the defects of traditional modeling method, high-precision Dynamic Modeling can be not only realized, and can substantially shorten the lead time.
Description
Technical field
The invention belongs to antenna technical field, and in particular to the large-scale antenna Dynamic Modeling side based on ANSYS and ADAMS
Method, for instructing the design of large-scale reflector antenna servo-drive system.
Background technology
Reflector antenna orients spoke as the most frequently used a kind of high-gain microwave and millimeter wave antenna by producing pencil beam
Energy is penetrated, is widely used in fields such as space communication, survey of deep space, radio astronomies.In order to more effectively explore one
A little tera incognitas, catch inevitably tends to more heavy caliber and Geng Gao from remote unlimited space information, reflector antenna
Working frequency.With the increase of antenna aperture and the raising of frequency, its corresponding targeted beam angle will narrow, if narrow ripple
Not in allowed band, the gain of potential raising will reduce rapidly the targeted precision of beam；Further, since antenna aperture is got over
Come bigger, antenna can be considered as a flexible structure in itself, its low-frequency resonant to the dynamic (dynamical) influence of antenna also increasingly
Substantially.The accurate foundation of reflector antenna integral power model improves control for the dynamic performance of further investigation antenna
Performance, improve pointing accuracy etc. and be respectively provided with important meaning.
The mass motion of reflector antenna includes elastic deformation and large-scale rigid motion by a small margin.In recent years, state
The inside and outside modeling deformed to structural elasticity by a small margin, which describes method, mainly to be had：(1) main free degree method：Guyan
RJ.Reduction of stiffness and mass matrices.AIAA Journal, 1965；3(2)：380-380 is carried
Since mass and rigidity "flop-out" method, substantial amounts of engineer rule of thumb, by the free degree of structure is divided into two classes：The main free degree and
From the free degree, the integrally-built free degree is replaced with a small amount of main free degree, so as to establishing the Structural Dynamics of a reduction
Model；Sau-Lon James Hu, Huangjun Li, Min Zhang.Refinement of reduced-models for
Dynamic systems, Progress in Natural Science, 2008 (18)：993-997 is according to principal and subordinate freedom degree
Method establishes the kinetic model of a multivariant spring-mass block system；Jia-Zhen Hong, Wei-Ming
Li.New iterative method for model updating based on model reduction,
Mechanical Systems and Signal Processing, 2011 (25)：180-192 is according to the method for principal and subordinate freedom degree
Establish the kinetic model of a solar energy sailboard；Drill pipe system non-linear dynamical behavior is studied in Kong Lingfei deep hole machinings, west
Pacify Polytechnics Ph.D. Dissertation, the extension of 2010 pairs of this method, it is proposed that a kind of based on free interface Modal Synthesis Technique
Degree of freedom in system reduction method, and establish more flexible revolution drilling rod oscillation crosswise models.(2) equivalent model method：This method is
Equivalent finite element method based on lumped mass and inertia.Kingliness soldier engineering machinery arm system Structural Dynamicses and characteristic research,
2014, Zhejiang University Ph.D. Dissertation establishes the dynamic differential equation of hydraulic excavating machinery arm based on the method；Zhang Tie
Bright satellites sandwich analysis and the Structural Design, 2012, Nanjing Aero-Space University Ph.D. Dissertation is for satellite and the rocket coupling
Structure is closed, analysis is designed using the complicated FEM model of equivalent model alternative structure；Zhang Junfei cannon structural parameters
Sensitivity analysis and optimizing research, 2014, Institutes Of Technology Of Nanjing's master thesis is directed to cannon structure, uses approximate model generation
Analysis and optimization is carried out for original Parameters of Finite Element model.By the research to the above method, summarize its weak point and exist
In：(1) for simple structure, its quality and stiffness matrix can be directly obtained, and structural dynamic is carried out according to as above method
It is feasible to learn modeling.However, for large-scale reflector antenna, up to ten thousand of the free degree of its FEM model, can not extract
Its corresponding matrix, therefore Dynamic Modeling can not be carried out based on as above method；(2) it is only applicable to structural system, and reflecting surface day
Line has typical rigid motion in motion process, and method as above does not apply to simultaneously.
The rigid motion and elastic vibration of reflector antenna are considered simultaneously, reflector antenna are modeled, both at home and abroad
The main roadmap of Research Literature be that elastic vibration and rigid body displacement are described respectively, then established by linear superposition whole
Body Model.Elastic vibration is mainly described in Modal Space by modal coordinate, and to the main rigid motion master of antenna
There is two ways：(1) only consider rigid motion the influence of inertia, ignore extraneous damping, W.Gawronski and completely
J.A.Mellstrom, " Elevation Control System Model for the DSS 13antenna " [J],
Ground Antennas and Facilities Engineering Section, TDA Progress Report 42-
106, May 15,1991,83-85. under this assumed condition antenna constant input will with constant acceleration movement,
With actually disagreing；(2) by emulating estimation damping, Zhang Jie, Huang Jin, a kind of large-scale day of the beautiful Control-oriented of Song Ruixue, Qiu Li
Line modeling method, 2013, (201310496650.5) Xian Electronics Science and Technology University, but the estimation needs to use antenna reality
Value, it is only applicable to after antenna builds up, is not suitable for the design phase.And both the above processing method, the rigid motion to antenna
And elastic vibration, the final linear superposition that carries out obtain mass motion, do not consider the coupled relation of both motions.It is but actual
In, for such a complicated object of reflector antenna, this thought based on linear superposition is modeled, and its precision is that have
To be investigated.Particularly when the pointing accuracy requirement of antenna is very high, in rad magnitude, this modeling method often meets not
Require.
In summary, currently without a kind of while consider the coupling of radar antenna rigid body displacement and elastic deformation, to realize
The kinetic description method of its integral power description.
The content of the invention
In view of the shortcomings of the prior art, the present invention is intended to provide a kind of large-scale antenna dynamics based on ANSYS and ADAMS
Modeling method, the rigid body displacement and elastic deformation and both of large-scale reflector antenna are considered based on ANSYS and ADAMS simultaneously
Coupling, to realize to the dynamic (dynamical) accurate description of large-scale reflector antenna, base is established for the SERVO CONTROL of large-scale reflector antenna
Plinth.
To achieve these goals, the present invention adopts the following technical scheme that：
Large-scale antenna dynamic modeling method based on ANSYS and ADAMS, comprises the following steps：
S1 establishes reflector antenna bullet for the concrete structure requirement of reflector antenna servo-drive system with reference to ANSYS softwares
The FEM model of property component, FEM model node number is nd；
S2 carries out model analysis according to following formula to step S1 elastic component FEM model：
Wherein, z (t),WithRespectively t describe generalized coordinates selected by reflector antenna structural vibration,
The first derivative and second dervative of generalized coordinates, i.e. nd× 1 displacement, speed, vector acceleration；M is nd×ndArchitecture quality
Matrix, C nd×ndStructural damping matrix, K nd×ndStructure stiffness matrix；
S3 is according to step S2 modal analysis result z (t)=φ ejwt, j=1,2 ..., nd, w and φ represent frequency respectively
Variable and modal displacement variable, extract each order frequency wiAnd the modal displacement φ corresponding to each order frequencyij, wherein i=1,
2 ..., nj, njThe rank number of mode blocked is represented, and separately constitutes frequency matrix Ω and vibration shape matrix Φ, is shown below：
S4 state space equations according to corresponding to step S3 result establishes the i-th rank modal vibration：
In formula,For state vector, qi(t) andRespectively the i-th rank mode is in t
Displacement coordinate and modal velocity coordinate；Ai、BiAnd CiSytem matrix respectively corresponding to the i-th rank modal vibration state space equation,
Input matrix and output matrix；U (t) is input power；
S5 equations according to obtained by parameter of structure design and step S4, calculate transmission function corresponding to the i-th rank mode subsystem
H2Norm | | Gi(w)||2：
||Gi(w)||2=| | Ci(jwI-Ai)-1Bi||2(i=1,2 ... nj)；
Wherein w is frequency variable, and showing above formula is calculated in frequency domain, and I is unit battle array；The norm reflects the i-th rank
The energy contribution degree that mode exports to total system；
S6 is incited somebody to action | | Gi(w)||2Arranged by order from big to small, according to required precision, k ranks before selection, corresponding section
Disconnected error is：
K rank mode of the S7 according to selected by step S6, with reference to ANSYS softwares, it is neutral to export mode corresponding to elastic component
File；
S8 steps for importing S7 in ADAMS softwares modal neutral file, and other rigid members of progress antenna successively
Modeling, and above modal neutral file and rigid member are attached by kinematic pair, it is whole to finally give reflector antenna
Body simulation model.
It should be noted that the reflector antenna elastic component FEM model described in step S1, corresponding reflector portion,
Specifically include principal reflection body, secondary reflector and support, centerbody, principal reflection body back frame structure, umbrella-type support, gear wheel and big
The counterweight of gear root.
It should be noted that in step S2, model analysis is applied with boundary condition, is revolved including release around antenna rigid body
Walk around the rotary freedom of axle, constrain the remaining free degree and to the simulation gear engagement of big little gear engagement place short beam, short beam
Non- end of engagement staff cultivation.
It should be noted that in step S3, the rank number of mode n that blocksjDetermined according to following calculating formula：
Wherein nmTo meet the rank number of mode of truncation condition, E (n) is mode energy corresponding to preceding n ranks mode, true by following formula
It is fixed：
kiAnd miRigidity and quality respectively corresponding to the i-th rank mode.
It should be noted that the sytem matrix A in step S4 after modei, input matrix BiAnd output matrix CiRespectively
Drawn according to following formula：
Bi=Φi Tbi；
Ci=ciΦi；
Wherein, ξiFor damping ratio, biFor nd× 1 input vector, the member of the node location at actuator is corresponded in the vector
Element puts one, other elements zero；ciFor 1 × ndOutput vector, the element of the node location in the vector at respective sensor puts
One, other elements zero；ΦiFor above-mentioned vibration shape matrix Φ the i-th row.
The beneficial effects of the present invention are：
1st, the present invention is based on ANSYS and ADAMS softwares simultaneously, while considers the rigid body displacement and bullet of large-scale reflector antenna
Property deformation description and its coupling, the accurate simulation model of large-scale reflector antenna is established, for setting for subsequent antenna servo-drive system
Meter has established solid foundation；
2nd, elastic deformation is described using modal coordinate method due to of the invention, and in Modal Space to influenceing to point to essence
The crucial mode of degree is chosen, and avoids directly too big by the scale of model caused by modal displacement description, Yi Jimo
State information is computationally intensive too much, it is difficult to the problem of solving；
3rd, simulation result shows, the present invention can effectively choose the mode being had a great influence to output, according to the mode of selection
Displacement, speed and the acceleration responsive all bases corresponding to state space reduction model and ANSYS complete model established
This coincide, and difference is very small, maximum relative error 5.47%, indicates the accuracy of the model of selected mode and foundation；
And operation time needed for reduced-order models substantially reduces, it is average 66% that the time reduces percentage, effectively entirely can may be used to large-scale
The dynamics of dynamic reflector antenna is described.
Brief description of the drawings
Fig. 1 is the flow chart of the present invention；
Fig. 2 is the structural representation of antenna in emulation experiment of the present invention
Fig. 3 is the FEM model schematic diagram of emulation experiment of the present invention；
Fig. 4 is each rank mode norm figure in emulation experiment modality selection of the present invention；
Fig. 5 is the kinetic model schematic diagram of emulation experiment of the present invention；
Fig. 6 is the driving moment schematic diagram of emulation experiment of the present invention；
Fig. 7 be emulation experiment of the present invention in Rigid-elastic Coupling dynamical simulation results schematic diagram, wherein Fig. 7 (a), Fig. 7 (b)
It is respectively angular displacement schematic diagram, angular speed schematic diagram and the angular acceleration signal of antenna azimuth and the angle of pitch with Fig. 7 (c)
Figure.
Embodiment
Below with reference to accompanying drawing, the invention will be further described, it is necessary to which explanation, the present embodiment is with this technology side
Premised on case, detailed embodiment and specific operating process are given, but protection scope of the present invention is not limited to this reality
Apply example.
As shown in figure 1, the large-scale antenna dynamic modeling method based on ANSYS and ADAMS, comprises the following steps：
S1 is required for the concrete structure of reflector antenna servo-drive system, and the elastic structure of antenna is established with reference to ANSYS softwares
The FEM model of part, including the support of reflector, minor face, centerbody, principal reflection body back frame structure, umbrella-type support and canine tooth
Wheel, the node number of FEM model is nd；
S2 applies boundary condition to step S1 FEM model, and boundary condition includes release around antenna rigid body rotating shaft
Rotary freedom, constrain the remaining free degree；Big little gear engagement place is engaged with short beam simulation gear, the non-end of engagement of short beam is complete
Constraint.Then model analysis is carried out according to following formula：
Wherein, z (t),WithRespectively t describe generalized coordinates selected by reflector antenna structural vibration,
The first derivative and second dervative of generalized coordinates, i.e. nd× 1 displacement, speed, vector acceleration；M is nd×ndAntenna structure
Mass matrix, C nd×ndAntenna structure damping matrix, K nd×ndAntenna structure stiffness matrix；
S3 is according to step S2 modal analysis result z (t)=φ ejwt, j=1,2 ..., nd, w and φ represent frequency respectively
Variable and modal displacement variable, extract each order frequency wiAnd the modal displacement φ corresponding to each order frequencyij, wherein i=1,
2 ..., nj, njThe rank number of mode blocked is represented, and separately constitutes frequency matrix Ω and vibration shape matrix Φ, is shown below：
The rank number of mode n wherein blockedjDetermined according to following calculating formula：
Wherein nmTo meet the rank number of mode of truncation condition, E (n) is mode energy corresponding to preceding n ranks mode, true by following formula
It is fixed：
kiAnd miRigidity and quality respectively corresponding to the i-th rank mode.
S4 state space equations according to corresponding to step S3 result establishes the i-th rank modal vibration of description：
In formula,For state vector, qi(t) andRespectively the i-th rank mode is in t
Displacement coordinate and modal velocity coordinate；Ai、BiAnd CiSytem matrix respectively corresponding to the i-th rank modal vibration state space equation,
Input matrix and output matrix；U (t) is input power；Ai、BiAnd CiDrawn respectively according to following formula：
Bi=Φi Tbi；
Ci=ciΦi；
Wherein, ξiFor damping ratio, biFor nd× 1 input vector, the member of the node location at actuator is corresponded in the vector
Element puts one, other elements zero；ciFor 1 × ndOutput vector, the element of the node location in the vector at respective sensor puts
One, other elements zero；ΦiFor above-mentioned vibration shape matrix Φ the i-th row.
S5 equations according to obtained by parameter of structure design and step S4, calculate transmission function corresponding to the i-th rank mode subsystem
H2Norm | | Gi(w)||2：
||Gi(w)||2=| | Ci(jwI-Ai)-1Bi||2(i=1,2 ... nj)；
Wherein w is frequency variable, and showing above formula is calculated in frequency domain, and I is unit battle array, and the norm reflects the i-th rank
The energy contribution degree that mode exports to total system；
S6 is incited somebody to action | | Gi(w)||2Arranged by order from big to small, according to required precision, k ranks before selection, corresponding section
Disconnected error is：
Modal neutral files of the S8 in ADAMS softwares in steps for importing S7, and other rigid structures of progress antenna successively
The modeling of part, above modal neutral file and rigid member are attached by kinematic pair, you can obtain antenna and integrally emulate
Model.
Advantages of the present invention can be further illustrated by following emulation：
By a kind of large-scale antenna dynamic modeling method based on ANSYS and ADAMS of the present invention, designed on certain antenna
Stage carries out simulation analysis, as shown in Fig. 2 the antenna includes principal reflection body 1, secondary reflector 3, minor face support 2, the principal reflection body back of the body
Frame structure 4, counterweight 5, mounting structures 6, umbrella-type support 7 and gear wheel 8.The bore of principal reflection body 1 of the antenna regards up to 100 meters
It is complete movable for elastomer, azimuth pitch.The FEM model of the antenna elastic component is as shown in Figure 3, it is desirable to establishes the antenna
Kinetic model.The intrinsic frequency of the antenna reflector is as shown in table 1, unit Hz.
Table 1
| Order | 1 | 2 | 3 | 4 | 5 |
| Intrinsic frequency | 0.6257 | 1.6591 | 1.6611 | 1.7877 | 1.8278 |
| Order | 6 | 7 | 8 | 9 | 10 |
| Intrinsic frequency | 1.8663 | 1.8814 | 1.9907 | 2.0802 | 2.0957 |
The rank number of mode n blocked according to step S3j=30, as the truncated error e of modality selection2When=0.1, each rank is calculated
The H of corresponding transmission function2Norm, the selection of crucial mode is carried out accordingly, as shown in Figure 4.Before and after modality selection, configuration is utilized
For dominant frequency 3.4Ghz, I3-2130CPU, the computer for inside saving as 2GB carries out the computing of impulse response, and average single operation time is such as
Shown in table 2 below：
Table 2
The steady-state value and error of impulse response are as shown in table 3：
Table 3
The two table data more than, after modality selection, Relative steady-state error is no more than 6%, but operation time is big
To reduce.
Modal neutral file corresponding to export, is conducted into ADAMS, and is combined with other rigid members, obtains day
The integral power simulation model of line.Antenna is as shown in Figure 5 to certain operating mode, its schematic diagram from level state setting in motion is referred to.
Actual antennas operation is slow start slow stop, applies driving moment as shown in Figure 6 in emulation；
From Fig. 7 (a) to Fig. 7 (c), based on the simulation model, azimuth and the angle of pitch are real-time during antenna movement
Angular displacement, angular speed and angular acceleration it is all available.
For those skilled in the art, technical scheme that can be more than and design, make various corresponding
Change and deform, and all these change and deformation should be construed as being included within the protection domain of the claims in the present invention.
Claims (3)
1. the large-scale antenna dynamic modeling method based on ANSYS and ADAMS, it is characterised in that comprise the following steps：
S1 establishes reflector antenna elasticity structure for the concrete structure requirement of reflector antenna servo-drive system with reference to ANSYS softwares
The FEM model of part, FEM model node number are nd；
S2 carries out model analysis according to following formula to step S1 elastic component FEM model：
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<mi>t</mi>
<mo>)</mo>
</mrow>
<mo>&rsqb;</mo>
<mo>}</mo>
</mrow>
<mfrac>
<mn>1</mn>
<mn>2</mn>
</mfrac>
</msup>
<mo>;</mo>
</mrow>
kiAnd miRigidity and quality respectively corresponding to the i-th rank mode；
S4 state space equations according to corresponding to step S3 result establishes the i-th rank modal vibration：
<mrow>
<mtable>
<mtr>
<mtd>
<mrow>
<mover>
<mi>x</mi>
<mo>&CenterDot;</mo>
</mover>
<mrow>
<mo>(</mo>
<mi>t</mi>
<mo>)</mo>
</mrow>
<mo>=</mo>
<msub>
<mi>A</mi>
<mi>i</mi>
</msub>
<mi>x</mi>
<mrow>
<mo>(</mo>
<mi>t</mi>
<mo>)</mo>
</mrow>
<mo>+</mo>
<msub>
<mi>B</mi>
<mi>i</mi>
</msub>
<mi>u</mi>
<mrow>
<mo>(</mo>
<mi>t</mi>
<mo>)</mo>
</mrow>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<mi>y</mi>
<mo>=</mo>
<msub>
<mi>C</mi>
<mi>i</mi>
</msub>
<mi>x</mi>
<mrow>
<mo>(</mo>
<mi>t</mi>
<mo>)</mo>
</mrow>
</mrow>
</mtd>
</mtr>
</mtable>
<mo>;</mo>
</mrow>
In formula,For state vector, qi(t) andDisplacement of respectively the i-th rank mode in t
Coordinate and modal velocity coordinate；Ai、BiAnd CiSytem matrix, input respectively corresponding to the i-th rank modal vibration state space equation
Matrix and output matrix；U (t) is input power；
Sytem matrix A after modei, input matrix BiAnd output matrix CiDrawn respectively according to following formula：
<mrow>
<msub>
<mi>A</mi>
<mi>i</mi>
</msub>
<mo>=</mo>
<mfenced open = "[" close = "]">
<mtable>
<mtr>
<mtd>
<mn>0</mn>
</mtd>
<mtd>
<mn>1</mn>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<mo>-</mo>
<msup>
<msub>
<mi>w</mi>
<mi>i</mi>
</msub>
<mn>2</mn>
</msup>
</mrow>
</mtd>
<mtd>
<mrow>
<mo>-</mo>
<mn>2</mn>
<msub>
<mi>&xi;</mi>
<mi>i</mi>
</msub>
<msub>
<mi>w</mi>
<mi>i</mi>
</msub>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
<mo>;</mo>
</mrow>
Bi=Φi Tbi；
Ci=ciΦi；
Wherein, ξiFor damping ratio, biFor nd× 1 input vector, the element that the node location at actuator is corresponded in the vector are put
One, other elements zero；ciFor 1 × ndOutput vector, the element of the node location in the vector at respective sensor puts one,
Other elements are zero；ΦiFor above-mentioned vibration shape matrix Φ the i-th row；
S5 equations according to obtained by parameter of structure design and step S4, calculate the H of transmission function corresponding to the i-th rank mode subsystem2Model
Number | | Gi(w)||2：
||Gi(w)||2=| | Ci(jwI-Ai)-1Bi||2(i=1,2 ... nj)；
Wherein w is frequency variable, and showing above formula is calculated in frequency domain, and I is unit battle array；The norm reflects the i-th rank mode
To the energy contribution degree of total system output；
S6 is incited somebody to action | | Gi(w)||2Arranged by order from big to small, according to required precision, k ranks before selection are corresponding to block mistake
Difference is：
<mrow>
<msub>
<mi>e</mi>
<mn>2</mn>
</msub>
<mo>=</mo>
<msup>
<mrow>
<mo>(</mo>
<munderover>
<mo>&Sigma;</mo>
<mrow>
<mi>i</mi>
<mo>=</mo>
<mi>k</mi>
<mo>+</mo>
<mn>1</mn>
</mrow>
<msub>
<mi>n</mi>
<mi>j</mi>
</msub>
</munderover>
<mo>|</mo>
<mo>|</mo>
<msub>
<mi>G</mi>
<mi>i</mi>
</msub>
<mo>(</mo>
<mi>w</mi>
<mo>)</mo>
<mo>|</mo>
<msub>
<mo>|</mo>
<mn>2</mn>
</msub>
<mo>)</mo>
</mrow>
<mrow>
<mn>1</mn>
<mo>/</mo>
<mn>2</mn>
</mrow>
</msup>
<mo>;</mo>
</mrow>
K rank mode of the S7 according to selected by step S6, with reference to ANSYS softwares, export modal neutral file corresponding to elastic component；
S8 steps for importing S7 in ADAMS softwares modal neutral file, and building for other rigid members of antenna is carried out successively
Mould, and above modal neutral file and rigid member are attached by kinematic pair, finally give reflector antenna and integrally imitate
True mode.
2. the large-scale antenna dynamic modeling method according to claim 1 based on ANSYS and ADAMS, it is characterised in that
Reflector antenna elastic component FEM model described in step S1, corresponding reflector portion, it is anti-to specifically include principal reflection body, pair
Beam and support, centerbody, principal reflection body back frame structure, umbrella-type support, the counterweight of gear wheel and gear wheel root.
3. the large-scale antenna dynamic modeling method according to claim 1 based on ANSYS and ADAMS, it is characterised in that
In step S2, model analysis is applied with boundary condition, the rotary freedom including release around antenna rigid body rotating shaft, about
The beam residue free degree and to big little gear engagement place with short beam simulation gear engage, the non-end of engagement staff cultivation of short beam.
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| CN105844018B (en) * | 2016-03-23 | 2019-03-19 | 西安电子科技大学 | A kind of choosing method of large size reflector antenna reflector pitching key mode |
| CN106202657B (en) * | 2016-06-30 | 2019-04-23 | 西安电子科技大学 | The electrical behavior prediction method of Blast Loading lower plane array antenna |
| CN106354910B (en) * | 2016-08-22 | 2019-07-26 | 西安电子科技大学 | A kind of structure master mode towards active phase array antenna determines method |
| CN107562988A (en) * | 2017-07-20 | 2018-01-09 | 西安电子科技大学 | A kind of large-scale truss vibration damping driving force optimization method |
| CN109190266B (en) * | 2018-09-10 | 2022-12-06 | 石家庄铁道大学 | Multi-rigid-body dynamics simplified modeling method based on ADAMS software |
| CN109522622B (en) * | 2018-10-31 | 2023-04-18 | 中国运载火箭技术研究院 | Method and system for determining on-orbit load working condition of multi-degree-of-freedom solar cell array |
| CN112001038B (en) * | 2020-06-24 | 2023-03-31 | 中国科学院新疆天文台 | Method for determining adjustment quantity of active main reflector antenna actuator based on panel adjustment matrix |
| CN112164895B (en) * | 2020-08-28 | 2022-02-01 | 西安空间无线电技术研究所 | Umbrella-shaped reflector dragged by passive slow-release unfolding mechanism |
| CN113609720B (en) * | 2021-07-07 | 2022-10-25 | 广州中望龙腾软件股份有限公司 | Master-slave degree of freedom processing method, device and storage medium for finite element analysis |
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