CN106557633A - Satellite sun wing sensor placement method is realized based on EI methods - Google Patents
Satellite sun wing sensor placement method is realized based on EI methods Download PDFInfo
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- CN106557633A CN106557633A CN201611076513.6A CN201611076513A CN106557633A CN 106557633 A CN106557633 A CN 106557633A CN 201611076513 A CN201611076513 A CN 201611076513A CN 106557633 A CN106557633 A CN 106557633A
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Abstract
The invention discloses a kind of acceleration transducer layout method towards the satellite sun wing, comprises the steps：Some initial measuring points are chosen by the topology layout feature of the satellite sun wing and constructs modal matrix Φ；Take estimation error covariance minimum as best estimate construction independent modal matrix A；Eigenvalues Decomposition is done to A the big order of contribution degree is extracted as preferred measuring point；With reference to sensor weight and reliability on solar wing requirement so that it is determined that the optimal location method of satellite sun wing mode measuring point.The present invention can realize the optimal sensor arrangement of solar wing mode inflight measurement, it is ensured that the realization of in-orbit mode measurement.
Description
Technical field
The present invention relates to sensor placement field, in particular it relates to the sensor cloth of the in-orbit mode measurement of the satellite sun wing
Office's method.
Background technology
Current satellite platform generally employs large scale and scratches greatly to adapt to high power and high-resolution mission requirements
Property solar battery array or deployable antenna, these flexible appendages cause satellite structure dynamic trait, and especially low frequency characteristic is complicated
Change.Thus real-time tracking is carried out in space and its dynamic property is carried out real-time identification to seem very heavy to sun battle array structure
Will, and China is in the stage of initial stage for the sensor placement that the modal identification of solar wing is carried out.
, there is problems with the mode measurement sensor layout of the satellite sun wing at present：
1) limited by ground experiment condition, it is impossible to accurately and reliably represent the in-orbit state of solar wing, cause whole star to design
In journey, reliability is higher or low so that during sensor placement, parameter is inconsistent with in-orbit practical situation, and existing can
By sex chromosome mosaicism；
2) lack the sensor placement method for the in-orbit low frequency measurement of solar wing.
The content of the invention
For defect of the prior art, it is an object of the invention to provide based on EI methods, a kind of realize that the satellite sun wing is sensed
Device layout method, by the sun wing model for setting up the high sensor attachment to be configured of accuracy, determines that needs are distinguished according to demand
The rank number of mode of knowledge, analyzes the structural constraint of adnexa, removes the position for being macroscopically unable to sensors configured, extracts rest position
Data of Mode, and Mode Shape matrix is constituted, the structural constraint of adnexa is analyzed, removes the position for being macroscopically unable to sensors configured
Put, extract the Data of Mode of rest position, and constitute Mode Shape matrix, using Optimum sensor placement criterion to configuration result
Evaluated, be iterated preferably, until realizing satisfactory results according to evaluation result.
For achieving the above object, the present invention is achieved by the following technical solutions.
One kind realizes satellite sun wing sensor placement method based on EI methods, comprises the steps：
Step S1, some initial measuring points are chosen by the topology layout feature of the satellite sun wing construct modal matrix Φ；
Step S2, take that estimation error covariance is minimum to construct independent modal matrix A as best estimate；
Step S3, Eigenvalues Decomposition is done to A the big order of contribution degree is extracted as preferred measuring point；
Step S4, with reference to sensor weight and reliability on solar wing requirement so that it is determined that satellite sun wing mode measuring point
Optimal location method.
Preferably, node location of the initial measuring point when selecting not close to solar wing, and its average driving freedom
Degree shift value is larger.
Preferably, methods described measurement is mode under in-orbit state, and the selection of initial sensor measuring point need to ensure too
Not interfering under two states is opened and draws in the positive span.
Preferably, the sensor measurement of arrangement is in-orbit solar wing acceleration information, according to the mode of in-orbit solar wing
Feature, the signal of collection concentrate on low frequency.
Preferably, sensor placement position measurement direction is the vertical of solar wing.
Preferably, the EI methods for using carry out sensor placement and comprise the steps：
Step S41, select average driving degree of freedom shift value it is larger, meet the initial measuring point of solar wing layout requirements；
Step S42, according to initial measuring point structural theory model modal matrix；
Step S43, construction independent modal matrix, and realize Eigenvalues Decomposition；
Step S44, effective Independent Vector is extracted using EI methods, remove the little element of contribution degree and degree of freedom；
Step S45, configuration result is entered using modal assurance criterion criterion, FI SHER Information Matrixes indexs and Singularity Value Index
Row is evaluated, and is iterated preferably, until realizing satisfactory results according to evaluation result.
Compared with prior art, the present invention has the advantages that：
With strong points, the sensor placement method is adapted to the in-orbit mode measurement of the satellite sun wing.In-orbit condition is sensor
Theoretical selection of the selection of measurement scheme, Optimum sensor placement etc. brings many constraints, also the installation position to sensor
Put, the quality and quantity of sensor, sensing data amount size propose very many requirements.Sensor placement proposed by the present invention
Method has little number, light weight, high reliability.
Sensor of the invention layout method, as long as carrying out adaptation to the solar wing placement scheme of different satellites,
The requirement of different model satellite sun wing modal identification can just be met, with higher versatility, had a extensive future.
Description of the drawings
Detailed description non-limiting example made with reference to the following drawings by reading, the further feature of the present invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the schematic flow sheet that the present invention realizes satellite sun wing sensor placement method based on EI methods.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, some deformations and improvement can also be made.These belong to the present invention
Protection domain.
Present embodiments provide one kind and satellite sun wing sensor placement method is realized based on EI methods, comprise the steps：
The sun wing model of the high sensor attachment to be configured of accuracy is set up, the rank number of mode for needing identification is determined according to demand, point
The structural constraint of analysis adnexa, removes the position for being macroscopically unable to sensors configured, extracts the Data of Mode of rest position, and constitutes
Mode Shape matrix, analyzes the structural constraint of adnexa, removes the position for being macroscopically unable to sensors configured, extracts rest position
Data of Mode, and Mode Shape matrix is constituted, configuration result is evaluated using Optimum sensor placement criterion, according to evaluation
As a result it is iterated preferably, until realizing satisfactory results.
Specially：
Step S1, some initial measuring points are chosen by the topology layout feature of the satellite sun wing construct modal matrix Φ；
Step S2, take that estimation error covariance is minimum to construct independent modal matrix A as best estimate；
Step S3, Eigenvalues Decomposition is done to A the big order of contribution degree is extracted as preferred measuring point；
Step S4, with reference to sensor weight and reliability on solar wing requirement so that it is determined that satellite sun wing mode measuring point
Optimal location method.
Node location of the initial measuring point when selecting not close to solar wing, and its average driving degree of freedom shift value
It is larger.
Methods described measurement is mode under in-orbit state, and the selection of initial sensor measuring point need to ensure solar wing spreading
With not interfering under gathering two states.
The sensor measurement of arrangement is in-orbit solar wing acceleration information, according to the Modal Features of in-orbit solar wing, is adopted
The signal of collection concentrates on low frequency.
Sensor placement position measurement direction is vertical for solar wing.
The EI methods for using carry out sensor placement and comprise the steps：
Step S41, select average driving degree of freedom shift value it is larger, meet the initial measuring point of solar wing layout requirements；
Step S42, according to initial measuring point structural theory model modal matrix；
Step S43, construction independent modal matrix, and realize Eigenvalues Decomposition；
Step S44, effective Independent Vector is extracted using EI methods, remove the little element of contribution degree and degree of freedom；
Step S45, configuration result is entered using modal assurance criterion criterion, FI SHER Information Matrixes indexs and Singularity Value Index
Row is evaluated, and is iterated preferably, until realizing satisfactory results according to evaluation result.
Below in conjunction with the accompanying drawings the present embodiment is further described.
As shown in figure 1, the present embodiment provide satellite sun wing sensor placement method is realized based on EI methods, specifically include
Following steps：
Primary election measuring point
Some initial measuring points are chosen by the topology layout feature of the satellite sun wing and the rank number of mode that need to be recognized, it is initial to pass
The selection of sensor measuring point need to ensure solar wing spreading and draw not interfering under two states in.
Calculate average driving degree of freedom shift value
Average driving degree of freedom shift value the greater of primary election measuring point is chosen, the measuring point near node is excluded.
Structural theory model modal matrix
By the measuring point of primary election, structural theory model modal matrix.
Covariance minimum matrix
Take theoretical model modal matrix estimation error covariance minimum as best estimate construction independent modal matrix A.
Eigenvalues Decomposition
Eigenvalues Decomposition is done to A the big order of contribution degree is extracted as preferred measuring point.
Configuration result is evaluated
According to interpretational criteria, require to obtain optimal location with reference to solar wing.
What the present embodiment was provided realizes satellite sun wing sensor placement method based on EI methods, by the knot of the satellite sun wing
Structure layout characteristics are chosen some initial measuring points and construct modal matrix Φ, take estimation error covariance minimum as best estimate structure
Independent modal matrix A is made, and Eigenvalues Decomposition is done to A and the big order of contribution degree is extracted as preferred measuring point, sensed with reference on solar wing
The requirement of the amount of thinking highly of and reliability is so that it is determined that the optimal location method of satellite sun wing mode measuring point.Solve solar wing in-orbit
The not high problem of mode measurement sensor layout adaptability, it is ensured that the installation site of in-orbit sensor, the quantity of sensor and matter
Amount meets the requirement of in-orbit modal test.
Above the specific embodiment of the present invention is described.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various modifications or modification within the scope of the claims, this not shadow
Ring the flesh and blood of the present invention.
Claims (6)
1. one kind realizes satellite sun wing sensor placement method based on EI methods, it is characterised in that comprise the steps：
Step S1, some initial measuring points are chosen by the topology layout feature of the satellite sun wing construct modal matrix Φ；
Step S2, take that estimation error covariance is minimum to construct independent modal matrix A as best estimate；
Step S3, Eigenvalues Decomposition is done to A the big order of contribution degree is extracted as preferred measuring point；
Step S4, with reference to sensor weight and reliability on solar wing requirement so that it is determined that satellite sun wing mode measuring point most
Excellent layout method.
2. it is according to claim 1 that satellite sun wing sensor placement method is realized based on EI methods, it is characterised in that described
Node location of the initial measuring point when selecting not close to solar wing, and its average driving degree of freedom shift value is larger.
3. it is according to claim 1 that satellite sun wing sensor placement method is realized based on EI methods, it is characterised in that described
Method measurement is mode under in-orbit state, and the selection of initial sensor measuring point need to ensure solar wing spreading and draw two kinds of shapes in
Not interfering under state.
4. it is according to claim 1 that satellite sun wing sensor placement method is realized based on EI methods, it is characterised in that arrangement
Sensor measurement be in-orbit solar wing acceleration information, according to the Modal Features of in-orbit solar wing, the signal of collection is concentrated
In low frequency.
5. it is according to claim 1 that satellite sun wing sensor placement method is realized based on EI methods, it is characterised in that sensing
Device placement position measurement direction is vertical for solar wing.
6. it is according to claim 1 that satellite sun wing sensor placement method is realized based on EI methods, it is characterised in that described
The EI methods for using carry out sensor placement and comprise the steps：
Step S41, select average driving degree of freedom shift value it is larger, meet the initial measuring point of solar wing layout requirements；
Step S42, according to initial measuring point structural theory model modal matrix；
Step S43, construction independent modal matrix, and realize Eigenvalues Decomposition；
Step S44, effective Independent Vector is extracted using EI methods, remove the little element of contribution degree and degree of freedom；
Step S45, configuration result is commented using modal assurance criterion criterion, FISHER Information Matrixes index and Singularity Value Index
Valency, is iterated preferably, until realizing satisfactory results according to evaluation result.
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| CN201611076513.6A CN106557633A (en) | 2016-11-29 | 2016-11-29 | Satellite sun wing sensor placement method is realized based on EI methods |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107515980A (en) * | 2017-08-18 | 2017-12-26 | 西安电子科技大学 | Two step sequence strain transducer Optimal Deployment Methods of structure-oriented deformation reconstruct |
| CN107609296A (en) * | 2017-09-25 | 2018-01-19 | 上海卫星工程研究所 | Satellite sun wing sensor placement method is realized based on QR decomposition methods |
| CN114943144A (en) * | 2022-05-17 | 2022-08-26 | 中国人民解放军军事科学院国防科技创新研究院 | Satellite layout optimization design method for distance control by utilizing Phi function |
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| CN104991982A (en) * | 2015-04-16 | 2015-10-21 | 北京理工大学 | Aircraft aeroelasticity inertia sensor layout method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107515980A (en) * | 2017-08-18 | 2017-12-26 | 西安电子科技大学 | Two step sequence strain transducer Optimal Deployment Methods of structure-oriented deformation reconstruct |
| CN107515980B (en) * | 2017-08-18 | 2021-03-23 | 西安电子科技大学 | Two-step sequence strain sensor optimized layout method for structural deformation reconstruction |
| CN107609296A (en) * | 2017-09-25 | 2018-01-19 | 上海卫星工程研究所 | Satellite sun wing sensor placement method is realized based on QR decomposition methods |
| CN114943144A (en) * | 2022-05-17 | 2022-08-26 | 中国人民解放军军事科学院国防科技创新研究院 | Satellite layout optimization design method for distance control by utilizing Phi function |
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Application publication date: 20170405 |