CN106446385A - Method for analyzing in-orbit vibration of cable-mesh reflector space-borne antenna - Google Patents
Method for analyzing in-orbit vibration of cable-mesh reflector space-borne antenna Download PDFInfo
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- CN106446385A CN106446385A CN201610824298.7A CN201610824298A CN106446385A CN 106446385 A CN106446385 A CN 106446385A CN 201610824298 A CN201610824298 A CN 201610824298A CN 106446385 A CN106446385 A CN 106446385A
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Abstract
The invention discloses a method for analyzing in-orbit vibration of a cable-mesh reflector space-borne antenna. The method comprises the following steps: inducing and resolving the cable-mesh reflector space-borne antenna into basic parts with certain functions; describing the geometrical features of each part and extracting the geometrical information of each part to complete finite element modeling of heat and structure; calculating the antenna in-orbit temperature field distribution and the time history of temperature field distribution of antenna entering and exiting a shadow region by utilizing orbit parameters; performing transient dynamic analysis and static analysis of the space-borne antenna, and calculating thermotropic transient vibration; establishing the linear approximate relation of electrical performance and vibration features; and determining the electrical performance variation when the antenna enters and exits the shadow region. The method realizes quick modeling to improve the analysis efficiency of in-orbit vibration of the cable-mesh reflector space-borne antenna; main geometrical information of the antenna can be described by simple lines and areas, so that the geometrical description of the antenna structure is simplified, and partition of finite element meshes in multi-field analysis can be benefited.
Description
Technical field
The invention belongs to Radar Antenna System field, the more particularly to in-orbit vibration analysis of a kind of cable mesh reflector satellite antenna
Method.
Background technology
At present, cable mesh reflector antenna is one of national defence and the indispensable equipment of space industry, due to its size and matter
Huge advantage in amount, frequently uses cable mesh reflector antenna, leads to for space exploration, satellite on the spacecraft such as various satellites
The fields such as letter, earth observation, electronic reconnaissance.Large deployable antenna structure in severe outer space environment, periodically
The sunshine area of ± 200 DEG C of experience and shadow region, cause structure to produce periodic thermal deformation and thermal stress.Shade is especially into and out
The thermal force on antenna is acted on during area and can produce mutation, so as to cause the thermal vibration of structure.Because its sensitivity and thermally-stabilised
Property require very high, the distorted reflector that thermal force causes can make antenna electric performance extreme degradation；Meanwhile, the mutation of thermal force causes
Thermal vibration can also affect the aloft gesture stability of antenna in rail.If making satellite antenna be on active service in severe spatial environmentss
Expected performance indications are reached in journey, are needed to carry out comprehensive simulating analysis to the heat structure electricity of antenna, are that Practical Project is carried
For reasonable effective information, the operation link such as electrical property compensation and attitude regulation and control is instructed.
Satellite antenna analysis model be properties are emulated and comprehensive analysis basis, but existing modeling and
Analysis method has more limitation, is embodied in the following aspects：
(1) it mostly is during tradition modeling and single entities model is modeled, it is impossible in view of the globality of antenna full model
And systematicness.
(2) relatively independent during model during each field analysis, this can cause the connecting of analysis model poor, and not
The feature of antenna system multi- scenarios method can be embodied.
(3) its thermal-induced deformation under warm load is acted on being only taken into account during the in-orbit thermal force of traditional analysis antenna, ignores its heat
Cause the feature of transient oscillation.
(4) tradition for satellite antenna Electrical Analysis, be using certain moment antenna deformation after reflecting surface node letter
Breath is solved.When the deformation real-time change of antenna, need structural analyses to be carried out to which in real time, then obtain corresponding electromagnetism
Performance, ceaselessly repeats this process.It will be apparent that this analysis antenna in-orbit vibration when electrical property method inefficiency, consumption
When effort, and equivalent to each time calculate be static deformation superposition, can not embody in-orbit vibration when antenna electric
The Variation Features of performance.
Content of the invention
It is an object of the invention to overcoming the shortcomings of above-mentioned existing method, a kind of cable mesh reflector satellite antenna is provided in-orbit
Vibration analysis method.
The present invention is achieved in that the in-orbit vibration analysis method of the cable mesh reflector satellite antenna includes following step
Suddenly：
Step one, cable mesh reflector satellite antenna is concluded the essential part being decomposed into certain function；
Step 2, describes the geometrical property of each several part and extracts each several part geological information, according to connected portion and connection
The link information of position point coordinates and each several part cell attribute, material properties, size attribute, realize in heat and structural analyses
FEM meshing and connection between FEM (finite element) model each several part, completes the finite element modeling of heat and structure；
Step 3, calculates the in-orbit thermo parameters method of antenna using orbit parameter, and antenna turnover shadow region temperature field is divided
The time history of cloth；
Step 4, the temperature field time history that analysis is obtained is loaded on structural finite element model as temperature loading,
Set damped coefficient, load step-length, integration step and initial condition is set up, carry out Transient Dynamics and the statics of satellite antenna
Analysis, analysis draws the vibration displacement information of antenna node, completes the heat-driven oscillation analysis of antenna under time varying temperature load；
Step 5, according to not deformed when reflector shape carry out the electrical property FEM meshing of reflecting surface, emulation
Calculate antenna per first-order modal sensitive matrix of the deformation to antenna spindle direction coefficient, it is established that the line of electrical property and vibration characteristics
Property approximation relation；Become the linear superposition that heat-driven oscillation response of changing commanders is launched into each first order mode using modal coordinate, according to above-mentioned
Every first-order modal coordinate after sensitive matrix and expansion obtains electrical property change during antenna turnover shadow region.
Further, the essential part includes：Flexible mounting arm, hoop truss component, rope net, reflection silk screen and truss connect
Head.
Further, the geometrical property straight line of the flexible mounting arm and the set description on the face of cylinder；The hoop truss
The geometrical property of component and rope net is all with the set description of straight line；The collection of the geometrical property triangle projective planum of the reflection silk screen
Close description；The geometrical property of the Truss joint is described with the three-dimensional set of thin-walled.
Further, the geological information of straight line is two-end-point information；The geological information on the face of cylinder is face of cylinder axis two-end-point
Information and cylinder radius surface；The geological information of triangle projective planum is the information on Atria summit；The geometry letter of thin-walled solid
Breath is directly represented with Pro/E graphic file；The geological information of each point includes numbering a little and space coordinatess.
Further, according to antenna flexible mounting arm, hoop truss component, rope net and the tetrameric geometry letter of reflection silk screen
Breath carries out Structural Finite Element Analysis stress and strain model；Pro/E graphic file according to Truss joint part has to Truss joint
The first stress and strain model of limit.Wherein, flexible mounting arm, hoop truss component, rope net and reflection four part of silk screen carry out structural capacity credit
During analysis FEM meshing, straight line carries out FEM meshing with spatial beam, and face of cylinder shell unit carries out limited
First stress and strain model, triangle projective planum carries out stress and strain model with the film unit for being only capable of unidirectional tension；Hoop truss component connector part
FEM meshing is carried out using solid shell element, and retrieves link information set.
Further, described heat-driven oscillation analysis is referred to, carries out transient state to satellite antenna respectively under temperature loading effect
Thermic dynamic response is finally deducted the quiet deformation of thermic and obtains thermic transient oscillation composition by kinetics and statics Analysis.
Further, the detailed process for solving electrical property in described step five has several steps as follows：
5a) firstly, since the in-orbit Oscillation Amplitude very little of antenna structure, by major axes orientation coefficient with respect to surface node position
Shift-in row first-order linear is approximate：
G=G0+KΔr (1)
Wherein, G is antenna spindle direction coefficient, G0For antenna spindle direction coefficient ideally, Δ r is surface section
Point displacement, K is first derivative column vector of the antenna spindle direction coefficient to modal displacement.
5b) as antenna structure degree of freedom is huge, structural vibration deformation is transformed into by modal coordinate using mode superposition method
In be analyzed.Therefore modal displacement can be described as the superposition of each rank mode of oscillation：
Wherein, Φi(i=1,2 ..., n) for antenna structure the i-th rank mode of oscillation, qiFor corresponding modal coordinate, n is
Mode of concern deforms exponent number.
Formula (2) is substituted into the relation that formula (1) can obtain major axes orientation coefficient and modal coordinate：
Wherein,Represent derivative of the antenna spindle direction coefficient to modal coordinate.
5c) model analyses are carried out to antenna, the front n rank mode of oscillation of day linearly coupled is obtained, may for every first-order modal
Maximum distortion, by mode of oscillation ΦiAnd modal coordinateGenerate the deformation of corresponding antenna structureAccording to change
Reflection line position after shape obtains the major axes orientation coefficient G of antenna using Electrical Analysis software analysisi, obtained by calculus of finite differences：
I=1 is taken successively, 2, n, you can obtain each coefficient in formula (3)
5d) in-orbit heat-driven oscillation analysis is carried out using mode superposition method to antenna structure, carry out modal coordinate conversion and obtain
Time-varying modal coordinate q under each rank vibratory responsei(t), (i=1,2 ..., n), aerial system is obtained by being substituted into (3) formula
The in-orbit major axes orientation index variation situation by during thermal force of system.
The in-orbit vibration analysis method of cable mesh reflector satellite antenna that the present invention is provided, it is intended to trifling geometry can be avoided
The repeated modelling operability of element, while increasing the connecting of each field analysis model, improves cable mesh reflector satellite antenna in-orbit
Heat structure electricity many field analysis efficiency of vibration, instructs Practical Project and its electrical property compensation and attitude regulation and control etc. is operated anti-
Feedback effective information.
The present invention is concluded, for the feature of cable mesh reflector satellite antenna, five bases being decomposed into certain function
This part, has included enough information in essential part, can automatically generate many field analysis model using these information, realizes
The automatic transmission of data and analysis result between many；When needing to change antenna model, the geometry of appropriate section only need to be simply changed
Parameter, it is to avoid the repetitive operation of trifling geometric element, it is achieved that rapid modeling, improves cable mesh reflector satellite antenna
Heat structure electricity many field analysis efficiency of in-orbit vibration；The main geological information of antenna is all described using simple line, face,
Both the antenna geometric description of structure, and division beneficial to during many field analysis finite element grid had been simplified.
The present invention solves its Transient Dynamics and statics response respectively when antenna heat-driven oscillation response is calculated, can
Effectively thermal-induced deformation and heat-driven oscillation is distinguished, preferably analyze its vibration characteristics.
The present invention is proposed using modal coordinate as connection electricity when electrical property of the antenna under in-orbit vibration operating mode is calculated
The bridge of performance and vibration performance.The method sets up the linear approximation pass of electrical property and vibration characteristics using sensitive matrix method
System, when antenna deformation real-time change, only need to calculate real-time modal coordinate, you can realize the lower antenna electric performance of in-orbit vibration
Quick analysis, is that the electrical performance characteristics under the in-orbit vibration of antenna provide reference.
Description of the drawings
Fig. 1 is the in-orbit vibration analysis method flow chart of cable mesh reflector satellite antenna provided in an embodiment of the present invention.
Fig. 2 is whole star system FEM (finite element) model provided in an embodiment of the present invention.
Fig. 3 is that cable mesh reflector satellite antenna essential part provided in an embodiment of the present invention is decomposed and geometrical property, geometry
Information and link information extract schematic diagram.
Fig. 4 is each when cable mesh reflector satellite antenna structure provided in an embodiment of the present invention, heat, electrical property finite element analyses
Partial Mesh divides the flow chart with being connected.
Fig. 5 is the method flow that phantom antenna provided in an embodiment of the present invention calculates electrical property change under heat-driven oscillation operating mode
Figure.
Fig. 6 be phantom antenna provided in an embodiment of the present invention turnover shader procedure in highest, the change of minimum, mean temperature
Change situation.
Fig. 7 is the Aberration nephogram in phantom antenna provided in an embodiment of the present invention deformation maximum moment.
Fig. 8 is the deformation song for deforming maximum node on emulation wire side provided in an embodiment of the present invention in the X, Y, Z direction
Line.
Fig. 9 is the heat-driven oscillation curve of the farthest end node of phantom antenna provided in an embodiment of the present invention.
Figure 10 is phantom antenna major axes orientation coefficient provided in an embodiment of the present invention with first and second order mode state changes in coordinates song
Line.
Figure 11 is that phantom antenna provided in an embodiment of the present invention major axes orientation coefficient when shadow region is passed in and out is changed over
Curve.
Specific embodiment
In order that the objects, technical solutions and advantages of the present invention become more apparent, with reference to embodiments, to the present invention
It is further elaborated.It should be appreciated that specific embodiment described herein is not used to only in order to explain the present invention
Limit the present invention.
Below in conjunction with the accompanying drawings the application principle of the present invention is explained in detail.
As shown in figure 1, the in-orbit vibration analysis method of the cable mesh reflector satellite antenna of the embodiment of the present invention includes following step
Suddenly：
S101：Cable mesh reflector satellite antenna is concluded hoop truss, rope net, reflection silk screen etc. is decomposed into certain work(
The essential part of energy；
S102：The geometrical property of description each several part simultaneously extracts each several part geological information, according to connected portion and connection position
Put the link informations such as point coordinates, realize in heat and structural analyses FEM meshing between FEM (finite element) model each several part and
Connection, completes the finite element modeling of heat and structure；
S103：The in-orbit thermo parameters method of antenna, particularly antenna turnover shadow region temperature are calculated using orbit parameter
The time history of field distribution；
S104：Will the temperature field time history that obtains of analysis as loading to structural finite element model on, carry out
Satellite antenna Transient Dynamics and statics Analysis, the in-orbit thermic transient oscillation situation being calculated under time varying temperature load；
S105：Using sensitive matrix method, antenna spindle directivity factor is expressed as the linear shape with antenna modal coordinate
Formula, solves its modal coordinate according to each moment deflection of cable mesh reflector satellite antenna, finally solves day using sensitive matrix
Line is in the major axes orientation coefficient in each moment.
Below in conjunction with the accompanying drawings the application principle of the present invention is further described.
With reference to Fig. 3,4, the present invention comprises the steps：
First, for the feature of cable mesh reflector satellite antenna, five for being decomposed into certain function are concluded basic
Part.With reference to Fig. 2, five essential parts include：Flexible mounting arm, hoop truss component, rope net, reflection silk screen and truss connect
Head.
2nd, the geometrical property of five parts of antenna is described, and extracts geological information and the link information of each several part.
With reference to Fig. 3, the geometrical property of flexible mounting arm is described with the set on straight line and the face of cylinder；Hoop truss component and
Set of the geometrical property of rope net all with straight line is describing；The geometrical property of reflection silk screen is retouched with the set of triangle projective planum
State；The geometrical property of Truss joint is described with the three-dimensional set of thin-walled.The geological information of straight line is two-end-point information；The face of cylinder
Geological information be face of cylinder axis two-end-point information and cylinder radius surface；The geological information of triangle projective planum is Atria
The information on summit；The geological information of thin-walled solid is directly represented with Pro/E graphic file.Additionally, the geological information of each point
Numbering and space coordinatess including point.Geometry connection between five parts that cable mesh reflector satellite antenna is decomposed is described as
The set of link information, link information includes to be connected the mark of two parts and the coordinate of link position point.
3rd, during structure mechanics analysis, flexible mounting arm according to antenna, hoop truss component, rope net and reflection silk screen four
Partial geological information carries out Structural Finite Element Analysis stress and strain model；According to the Pro/E graphic file of Truss joint part to purlin
Holder joint carries out FEM meshing.
With reference to Fig. 4, structural mechanics are being carried out to flexible mounting arm, hoop truss component, rope net and reflection four part of silk screen
During analysis finite element stress and strain model, straight line carries out FEM meshing with spatial beam, and the face of cylinder is had with shell unit
The first stress and strain model of limit, triangle projective planum carries out stress and strain model with the film unit for being only capable of unidirectional tension.Truss joint part is using real
Body shell unit carries out FEM meshing, and retrieves link information set, Truss joint with other parts each be connected
Create at position and increase node newly, newly-increased node is fixed together by short beam with node in adjacent domain, while specifying these
Newly-increased node is attached so as to the other parts with structure as interface node.
4th, link information set is traveled through, according to per bar link information, in two parts that antenna is connected, is looked into respectively
The node nearest away from link position point is looked for, i.e., achievable antenna finite element mould is coupled to all degree of freedom of the two nodes
Connection between type each several part, completes the finite element modeling work of structure.
5th, temperature field heat analysis process and structure mechanics analysis similar process, the flexible mounting arm according to antenna, periphery purlin
The geological information of frame member, rope net and reflection four parts of silk screen carries out temperature field heat analysis FEM meshing, while right
Truss joint part carries out FEM meshing, and realizes the connection between each several part, completes the finite element modeling work of heat.
Reference Fig. 4, straight line One-dimensional heat transfer dividing elements, the face of cylinder and triangle projective planum Two-Dimensional Heat Conduction unit are drawn
Point.Truss joint part carries out FEM meshing using heat conductor unit, while link information set is retrieved, in truss
Create at joint and each link position of other parts and increase node newly, the node in newly-increased node and adjacent domain is by one-dimensional
Heat transmission unit connects, using these newly-increased nodes as interface node.
6th, during heat-two field analysis of structure, using orbit parameter, the in-orbit thermo parameters method of antenna, particularly day are calculated
The time history of line turnover shadow region thermo parameters method, the temperature field time history that analysis is obtained is as loading to knot
In structure FEM (finite element) model, satellite antenna Transient Dynamics and statics Analysis are carried out, obtain under time varying temperature load in-orbit shakes
Dynamic deformation result and thermic transient oscillation result.
7th, during structure-electric two field analysis, according to not deformed when reflector shape carry out the electrical property finite element of reflecting surface
Stress and strain model, the simulation calculation antenna sensitive matrix of deformation to antenna spindle direction coefficient per first-order modal, it is established that electrical property
Linear approximation relation with vibration characteristics；Become heat-driven oscillation response of changing commanders using modal coordinate and be launched into the linear folded of each first order mode
Plus, electrical property when antenna passes in and out shadow region is obtained according to the every first-order modal coordinate after above-mentioned sensitive matrix and expansion to be become
Change.
With reference to emulation, the application effect of the present invention is explained in detail.
1. simulation object
Certain biasing Mesh reflector antenna, it is 25m that bore is 35m, focal length, and biasing height is 24m, feed using preferable
Gaussian feed (Gaussian-feed), L-band, x linear polarization is encouraged.
2. emulation content and result
When position of sun is in spring, autumnal equinoctial point, satellite is most long in the time for passing in and out shadow region in ground running.Select
The change of temperature field that day in the Spring Equinox whole star system is run is simulated in Earth's orbit.When position of sun is in the first point of Aries, Geo-synchronous rail
The shadow region total time in road is 4140s, enters 1000s before shadow region from antenna and starts to calculate, and the total time of calculating is 7200s.
Fig. 6 is to pass in and out the highest of whole star system, the situation of change of minimum, mean temperature in shader procedure.As can be seen that
The 1000s moment enter shadow region after whole star temperature be gradually lowered, through time more than ten minutes after carving shadow region in 5140s
Antenna temperature reaches steady statue.Fig. 7 is the Aberration nephogram in antenna deformation maximum moment；Fig. 8 is the section for deforming maximum on wire side
Deformation curve of the point on tri- directions of X, Y, Z.Fig. 9 is the heat-driven oscillation curve of the farthest end node of antenna.
The corresponding electrical property of deformation analytical calculation antenna for antenna reflective face during turnover shadow region.Select
1.5GHz carries out Electrical Analysis for working frequency points, and feed is located at design parabolic focus.Figure 10 is antenna spindle direction coefficient
With mainly each order mode state changes in coordinates curve.Figure 11 is that antenna major axes orientation coefficient when shadow region is passed in and out changes over song
Line.
Presently preferred embodiments of the present invention is the foregoing is only, not in order to limit the present invention, all essences in the present invention
Any modification, equivalent and improvement that is made within god and principle etc., should be included within the scope of the present invention.
Claims (7)
1. a kind of in-orbit vibration analysis method of cable mesh reflector satellite antenna, it is characterised in that the spaceborne day of the cable mesh reflector
The in-orbit vibration analysis method of line is comprised the following steps：
Step one, cable mesh reflector satellite antenna is concluded the essential part being decomposed into certain function；
Step 2, describes the geometrical property of each several part and extracts each several part geological information, according to connected portion and link position
The link information of point coordinates, realizes the FEM meshing between each several part and connection in heat and structural analyses, completes heat
Finite element modeling with structure；
Step 3, calculates the in-orbit thermo parameters method of antenna using orbit parameter, antenna turnover shadow region thermo parameters method
Time history；
Step 4, will the temperature field time history that obtains of analysis as loading to structural finite element model on, enter planet
Antenna Transient Dynamics and statics Analysis are carried, calculates thermic transient oscillation；
Step 5, according to not deformed when reflector shape carry out the electrical property FEM meshing of reflecting surface, simulation calculation
The antenna sensitive matrix of deformation to antenna spindle direction coefficient per first-order modal, it is established that electrical property is linear near with vibration characteristics
Like relation；Become the linear superposition that heat-driven oscillation response of changing commanders is launched into each first order mode using modal coordinate, according to above-mentioned sensitivity
Every first-order modal coordinate after matrix and expansion obtains electrical property change during antenna turnover shadow region.
2. the in-orbit vibration analysis method of cable mesh reflector satellite antenna as claimed in claim 1, it is characterised in that described basic
Part includes：Flexible mounting arm, hoop truss component, rope net, reflection silk screen and Truss joint.
3. the in-orbit vibration analysis method of cable mesh reflector satellite antenna as claimed in claim 2, it is characterised in that the flexibility
The geometrical property straight line of support arm and the set description on the face of cylinder；The geometrical property of the hoop truss component and rope net is all used
The set description of straight line；The set description of the geometrical property triangle projective planum of the reflection silk screen；The Truss joint several
What characteristic is described with the three-dimensional set of thin-walled.
4. the in-orbit vibration analysis method of cable mesh reflector satellite antenna as claimed in claim 3, it is characterised in that straight line several
What information is two-end-point information；The geological information on the face of cylinder is face of cylinder axis two-end-point information and cylinder radius surface；Triangle
The geological information of plane is the information on Atria summit；Thin-walled solid geological information directly with Pro/E graphic file come
Represent；The geological information of each point includes numbering a little and space coordinatess.
5. the in-orbit vibration analysis method of cable mesh reflector satellite antenna as claimed in claim 1, it is characterised in that according to antenna
Flexible mounting arm, hoop truss component, rope net and the reflection tetrameric geological information of silk screen carry out Structural Finite Element Analysis net
Lattice are divided；Pro/E graphic file according to Truss joint part carries out FEM meshing to Truss joint.
6. the in-orbit vibration analysis method of cable mesh reflector satellite antenna as claimed in claim 5, it is characterised in that flexible support
Arm, hoop truss component, rope net and reflection four part of silk screen carry out structure mechanics analysis FEM meshing, straight line space
Beam element carries out FEM meshing, and the face of cylinder carries out FEM meshing with shell unit, and triangle projective planum is with being only capable of list
Stress and strain model is carried out to the film unit of tension；Hoop truss component connector part carries out finite element grid using solid shell element and draws
Point, and retrieve link information set.
7. the in-orbit vibration analysis method of cable mesh reflector satellite antenna described in a kind of utilization claim 1-6 any one is spaceborne
The multi- scenarios method analysis method of the in-orbit vibration of antenna.
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