CN105486474A - Satellite flexible part on-orbit modal identification realization system and method - Google Patents
Satellite flexible part on-orbit modal identification realization system and method Download PDFInfo
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- CN105486474A CN105486474A CN201510860957.8A CN201510860957A CN105486474A CN 105486474 A CN105486474 A CN 105486474A CN 201510860957 A CN201510860957 A CN 201510860957A CN 105486474 A CN105486474 A CN 105486474A
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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Abstract
The invention provides a satellite flexible part on-orbit modal identification realization system and method. The realization system comprises a pulse excitation module, a signal acquisition module, a data transmission module, a satellite on-orbit vibration monitoring and modal identification module and a data processing module. The pulse excitation module is used for carrying out pulse excitation on a satellite flexible part; the signal acquisition module is used for collecting pulse response signals at the place of each measuring point on the satellite flexible part; the data transmission module is used for transmitting the pulse response signals of each measuring point to the ground; the satellite on-orbit vibration monitoring and modal identification module is used for receiving and monitoring the pulse response signals of each measuring point and collecting acceleration response signals generated by the satellite flexible part in the satellite on-orbit steady-state operation process; and the data processing module is used for carrying out modal frequency and modal vibration shape identification according to pulse response signals of each measuring point. The system and method solve the problem of inaccurate ground modal frequency measurement of the satellite flexible part; and the system is reliable and high in universality.
Description
Technical field
The present invention relates to the Modal Experimental Method in-orbit of satellite flexible part, particularly, what relate to the modal identification in-orbit of satellite flexible part realizes system and method.
Background technology
Current satellite platform is for adapting to high power and high-resolution mission requirements, and generally have employed solar battery array or the deployable antenna of the large flexibility of large scale, these flexible appendages make satellite structure kinematic behavior, and especially low frequency characteristic is complicated.Under the impact of some useful load rotating mechanism, because ground mode estimates deficiency, very likely cause the vibration of obvious attitude.The detection accuracy reducing space remote sensing equipment must even may cause attitude of satellite angle to occur larger change by this, is therefore necessary to carry out monitoring analysis to mode in-orbit.
, there is following problem in current satellite Modal Parameter Identification:
1) by the restriction that ground experiment condition and simulation parameter are arranged, whole star state in orbit can not be represented accurately and reliably, cause reliability in whole star design process higher or on the low side, make parameter in design process with actual conditions are inconsistent in-orbit, cause rail control to occur control deviation;
2) make the mode of some parts and whole star produce vibration coupling on the other hand, cause attitude stability to decline, affect work and the life-span of load and whole star, there is integrity problem, weak link and accident potential;
3) lack Modal Experimental Method, the especially in-orbit selection of modal test energisation mode in-orbit effectively, be a blank always.
Summary of the invention
For defect of the prior art, what the object of this invention is to provide a kind of modal identification in-orbit of satellite flexible part realizes system and method.
According to the invention provides satellite flexible part modal identification in-orbit realize system, comprising: pulse excitation module, signal acquisition module, data transmission module, satellite be vibration monitoring and modal idenlification module, data processing module in-orbit;
-described pulse excitation module, for carrying out pulse excitation to satellite flexible part;
-described signal acquisition module, comprises some sensors, and described some sensors are arranged on satellite flexible part and form measuring point, for gathering the impulse response signal of each measuring point position on satellite flexible part;
-described data transmission module, for being sent to ground by the impulse response signal of each measuring point;
-described satellite is vibration monitoring and modal idenlification module in-orbit, for receiving and monitor the impulse response signal of each measuring point;
-described data processing module, for carrying out the identification of model frequency and Mode Shape according to the impulse response signal of each measuring point.
Preferably, described pulse excitation module utilizes the thruster of Satellite attitude and orbit control to light a fire and causes pulse excitation to satellite flexible part.
Preferably, the mode of described thruster igniting is the positive and negative operating mode to the work of thruster sequencing, and according to actual requirement, by the duration of ignition of Dynamics Simulation Analysis determination thruster, the interval of twice duration of ignition when just spraying and regurgitating, and the operating mode of thruster igniting.
Preferably, described signal acquisition module also comprises: data collecting card, transmission line, and described data collecting card can change piezoelectric signal into digital signal, and described transmission line is anti-interference strip line.
An implementation method for the modal identification in-orbit of satellite flexible part, is characterized in that, comprise the steps:
Step 1: the analysis of dynamics Coupled Rigid-flexible is carried out to whole star, sets up the finite element model of whole star;
Step 2: after dynamics Coupled Rigid-flexible is analyzed, by using EffectiveIndependence, is called for short best measuring point needed for mould measurement on EI method determination flexible part, and in described best measuring point place placement sensor;
Step 3: in satellite stable state control procedure, carries out pulse excitation by the method for the thruster igniting making gesture stability use and orbits controlling to satellite flexible part;
Step 4: record each measuring point vibration response signal by sensor, and be sent to ground by number biography passage;
Step 5: vibration response signal inputs vibration monitoring and modal identification system in-orbit, carries out the identification of model frequency and Mode Shape.
Preferably, described satellite flexible part comprises solar battery array, satellite SAR antenna etc., when the method utilizing thruster to light a fire in wherein said step 3 carries out pulse excitation to satellite flexible part, described pulse enough evokes the Mode variation of flexible part, and described mode comprises frequency and the vibration shape of flexible part
Preferably, the mode of the thruster igniting in described step 3 is the positive and negative operating mode to the work of thruster sequencing, and according to actual requirement, by the duration of ignition of Dynamics Simulation Analysis determination thruster, the interval of twice duration of ignition when just spraying and regurgitating, and the operating mode of thruster igniting.
Preferably, the pulse excitation in described step 3 is the pulse width of 300ms, and described thruster is just spraying and regurgitating twice firing time interval and need be greater than 5s.
Compared with prior art, the present invention has following beneficial effect:
1, method provided by the invention can provide efficiently and effectively to encourage for modal test in-orbit, obtains reliable data result, the true mode of actual response satellite flexible part in-orbit under state.
2, system and method highly versatile provided by the invention, is applicable to other disturbance component modal test in-orbit.
3, utilize method provided by the invention can obtain satellite flexible part modal parameter in-orbit, described modal parameter in-orbit may be used for Platform Structure Design and satellite control system Modifying model after being input to satellite coupled vibrations characteristic analysis system.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the system chart of modal identification in-orbit for satellite flexible part provided by the invention;
Fig. 2 is the system architecture of the modal identification in-orbit schematic diagram for satellite flexible part provided by the invention.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
According to the invention provides satellite flexible part modal identification in-orbit realize system, comprising: pulse excitation module, signal acquisition module, data transmission module, satellite be vibration monitoring and modal idenlification module, data processing module in-orbit;
-described pulse excitation module, for carrying out pulse excitation to satellite flexible part;
-described signal acquisition module, comprises some sensors, and described some sensors are arranged on satellite flexible part and form measuring point, for gathering the impulse response signal of each measuring point position on satellite flexible part;
Particularly, institute's sensor is acceleration transducer, when being subject to the pulse excitation of lighter, can record the vibratory response of corresponding point position.
-described data transmission module, for being sent to ground by the impulse response signal of each measuring point;
-described satellite is vibration monitoring and modal idenlification module in-orbit, for receiving and monitor the impulse response signal of each measuring point;
-described data processing module, for carrying out the identification of model frequency and Mode Shape according to the impulse response signal of each measuring point.
Particularly, as shown in Figure 1, the present invention is by the signal picker of satellite vibration monitoring and mould measurement system in-orbit, obtain satellite in-orbit in steady state operation, the acceleration responsive signal that satellite flexible part produces by pulse excitation, then the signal utilizing the modal identification technology based on time domain response to be recorded by sensor carries out modal identification, thus determines the model frequency composition of the lower flexible parts of state in-orbit, solves the indeterminable problem of model frequency on flexible part ground.The present invention proposes a kind of satellite flexible part feasible, reliable energized process method of modal identification in-orbit, pulse excitation is carried out by thruster igniting, collection signal is analyzed by vibration monitoring and modal identification system in-orbit, is identified, thus complete the function of satellite model analysis in-orbit.
Preferably, described pulse excitation module utilizes the thruster of Satellite attitude and orbit control to light a fire and causes pulse excitation to satellite flexible part.
Preferably, the mode of described thruster igniting is the positive and negative operating mode to the work of thruster sequencing, and according to demand, is arranged the duration of ignition of thruster by Dynamics Simulation Analysis, the interval of twice duration of ignition when just spraying and regurgitating, and the operating mode of thruster igniting.
Particularly, in satellite stable state control procedure, by make gesture stability with and the thruster of the orbits controlling method of lighting a fire pulse excitation is carried out to tested flexible part, as the excitation of this flexible part modal test in-orbit.The mode of thruster igniting is the positive and negative operating mode to the work of thruster sequencing, the duration of ignition length i.e. the impact of pulse excitation width on frequency identification be mainly reflected in amplitude, pulse width is longer, responds more obvious, therefore selects the pulse width of 300ms.Just spraying and regurgitating twice firing time interval and need be greater than 5s, unsuitable long again, recommend 10s, the operating mode of thruster igniting need guarantee that the pulse excitation caused flexible part enough evokes flexible part at least first three rank mode, preferential recommendation driftage+rolling, or driftage+pitch channel.
Preferably, described signal acquisition module also comprises: data collecting card, transmission line, and described data collecting card can change piezoelectric signal into digital signal, and described transmission line is anti-interference strip line.
An implementation method for the modal identification in-orbit of satellite flexible part, is characterized in that, comprise the steps:
Step 1: the analysis of dynamics Coupled Rigid-flexible is carried out to whole star, sets up the finite element model of whole star;
Particularly, for solar battery array, solar battery array is flexible body, therefore when setting up the finite element model of whole star, can do suitably to simplify to model.
Step 2: after dynamics Coupled Rigid-flexible is analyzed, by using EffectiveIndependence, is called for short best measuring point needed for mould measurement on EI method determination flexible part, and in described best measuring point place placement sensor;
Step 3: in satellite stable state control procedure, carries out pulse excitation by the method for the thruster igniting making gesture stability use and orbits controlling to satellite flexible part;
Step 4: record each measuring point vibration response signal by sensor, and be sent to ground by number biography passage;
Step 5: vibration response signal inputs vibration monitoring and modal identification system in-orbit, carries out the identification of model frequency and Mode Shape.
When the method utilizing thruster to light a fire in described step 3 carries out pulse excitation to satellite flexible part, described pulse enough evokes flexible part Mode variation, and described mode comprises its model frequency and the vibration shape.
Particularly, the selection of the operating mode of thruster igniting can be completed by Dynamics Simulation Analysis, is obtained its sparking mode of reasoning that can motivate first three rank mode, comprise thruster fire group syntype by simulation analysis, the interval of twice duration of ignition when just spraying and regurgitating, and the operating mode of thruster igniting.
Preferably, the mode of the thruster igniting in described step 3 is the positive and negative operating mode to the work of thruster sequencing.
Preferably, the pulse excitation in described step 3 is the pulse width of 300ms, and described thruster is just spraying and regurgitating twice firing time interval and need be greater than 5s.
Particularly, as shown in Figure 2, uphole equipment passes passage by number and obtains impulse response signal, thus carries out identification to the modal parameter of solar battery array under state in-orbit.The sensor that satellite flexible part is arranged and data collecting card, data collecting card can change piezoelectric signal into digital signal, is the anti-interference shielding transmission realizing signal comprising transmission line, and data collecting card is the high-precision A/D conversion to signal.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (8)
1. satellite flexible part modal identification in-orbit realize a system, it is characterized in that, comprising: pulse excitation module, signal acquisition module, data transmission module, satellite be vibration monitoring and modal idenlification module, data processing module in-orbit;
-described pulse excitation module, for carrying out pulse excitation to satellite flexible part;
-described signal acquisition module, comprises some sensors, and described some sensors are arranged on satellite flexible part and form measuring point, for gathering the impulse response signal of each measuring point position on satellite flexible part;
-described data transmission module, for being sent to ground by the impulse response signal of each measuring point;
-described satellite is vibration monitoring and modal idenlification module in-orbit, for receiving and monitor the impulse response signal of each measuring point;-described data processing module, for carrying out the identification of model frequency and Mode Shape according to the impulse response signal of each measuring point.
2. satellite flexible part according to claim 1 modal identification in-orbit realize system, it is characterized in that, described pulse excitation module utilize the thruster of Satellite attitude and orbit control light a fire pulse excitation is caused to satellite flexible part.
3. satellite flexible part according to claim 2 modal identification in-orbit realize system, it is characterized in that, the mode of described thruster igniting is the positive and negative operating mode to the work of thruster sequencing, and according to the actual requirements, by the duration of ignition of Dynamics Simulation Analysis determination thruster, the interval of twice duration of ignition when just spraying and regurgitating, and the operating mode of thruster igniting.
4. satellite flexible part according to claim 1 modal identification in-orbit realize system, it is characterized in that, described signal acquisition module also comprises: data collecting card, transmission line, described data collecting card can change piezoelectric signal into digital signal, and described transmission line is anti-interference strip line.
5. an implementation method for the modal identification in-orbit of satellite flexible part, is characterized in that, comprise the steps:
Step 1: the analysis of dynamics Coupled Rigid-flexible is carried out to whole star, sets up the finite element model of whole star;
Step 2: after dynamics Coupled Rigid-flexible is analyzed, by using EffectiveIndependence, is called for short best measuring point needed for mould measurement on EI method determination flexible part, and in described best measuring point place placement sensor;
Step 3: in satellite stable state control procedure, carries out pulse excitation by the method for the thruster igniting making gesture stability use and orbits controlling to satellite flexible part;
Step 4: record each measuring point vibration response signal by sensor, and be sent to ground by number biography passage;
Step 5: vibration response signal inputs vibration monitoring and modal identification system in-orbit, carries out the identification of model frequency and Mode Shape.
6. the implementation method of the modal identification in-orbit of satellite flexible part according to claim 5, is characterized in that, described satellite flexible part comprises solar battery array, satellite SAR antenna.
7. the implementation method of the modal identification in-orbit of satellite flexible part according to claim 5, it is characterized in that, the mode of the thruster igniting in described step 3 is the positive and negative operating mode to the work of thruster sequencing, and demand, by the duration of ignition of Dynamics Simulation Analysis determination thruster, the interval of twice duration of ignition when just spraying and regurgitating, and the operating mode of thruster igniting.
8. the implementation method of the modal identification in-orbit of satellite flexible part according to claim 7, is characterized in that, the pulse excitation in described step 3 is the pulse width of 300ms, and described thruster is just spraying and regurgitating twice firing time interval and need be greater than 5s.
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| CN106557633A (en) * | 2016-11-29 | 2017-04-05 | 上海卫星工程研究所 | Satellite sun wing sensor placement method is realized based on EI methods |
| CN106557636A (en) * | 2016-11-30 | 2017-04-05 | 上海卫星工程研究所 | The model emulation method of sun battle array mode thruster excitation |
| CN106777587A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | For the measuring method of the lower flexible accessory vibration emulation of space environment |
| CN107194077A (en) * | 2017-05-25 | 2017-09-22 | 北京空间飞行器总体设计部 | A kind of computational methods for obtaining antenna arm vibration suppression response |
| CN107203663A (en) * | 2017-05-16 | 2017-09-26 | 北京空间飞行器总体设计部 | Compliant member points to acquisition methods under a kind of motor-driven effect of rail control |
| CN107941441A (en) * | 2017-11-14 | 2018-04-20 | 北京卫星环境工程研究所 | Determine the method that the in-orbit border of simulation influences the in-orbit dynamics of spacecraft |
| CN108573278A (en) * | 2018-03-14 | 2018-09-25 | 山东科技大学 | A kind of multiple operating modes process modal identification method |
| CN108986436A (en) * | 2018-06-19 | 2018-12-11 | 上海卫星工程研究所 | A kind of communication system for the transmission of Satellite Vibration data |
| CN109612664A (en) * | 2019-01-08 | 2019-04-12 | 上海卫星工程研究所 | The in-orbit vibrational state method and system of satellite flexible appendage is recognized using gyro data |
| CN109632185A (en) * | 2018-12-13 | 2019-04-16 | 上海航天控制技术研究所 | A kind of in-orbit estimation method of large inertia rotatable parts unbalance dynamic characteristic |
| CN109655218A (en) * | 2019-01-08 | 2019-04-19 | 上海卫星工程研究所 | With the method and system of the whole star flexible vibration modal frequency of satellite gyroscope data identification |
| CN109917797A (en) * | 2019-01-09 | 2019-06-21 | 上海卫星工程研究所 | Utilize the whole star flexible vibration modal damping method and system of satellite gyroscope data identification |
| CN111177885A (en) * | 2019-12-09 | 2020-05-19 | 上海航天控制技术研究所 | Ground experiment method for dynamic characteristics of formation of large flexible spacecraft |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106557633A (en) * | 2016-11-29 | 2017-04-05 | 上海卫星工程研究所 | Satellite sun wing sensor placement method is realized based on EI methods |
| CN106557636A (en) * | 2016-11-30 | 2017-04-05 | 上海卫星工程研究所 | The model emulation method of sun battle array mode thruster excitation |
| CN106777587A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | For the measuring method of the lower flexible accessory vibration emulation of space environment |
| CN106557636B (en) * | 2016-11-30 | 2019-09-17 | 上海卫星工程研究所 | The model emulation method of sun battle array mode thruster excitation |
| CN107203663A (en) * | 2017-05-16 | 2017-09-26 | 北京空间飞行器总体设计部 | Compliant member points to acquisition methods under a kind of motor-driven effect of rail control |
| CN107203663B (en) * | 2017-05-16 | 2021-02-09 | 北京空间飞行器总体设计部 | Flexible part pointing acquisition method under action of attitude and orbit control motor |
| CN107194077B (en) * | 2017-05-25 | 2021-02-09 | 北京空间飞行器总体设计部 | Calculation method for obtaining vibration suppression response of antenna arm |
| CN107194077A (en) * | 2017-05-25 | 2017-09-22 | 北京空间飞行器总体设计部 | A kind of computational methods for obtaining antenna arm vibration suppression response |
| CN107941441A (en) * | 2017-11-14 | 2018-04-20 | 北京卫星环境工程研究所 | Determine the method that the in-orbit border of simulation influences the in-orbit dynamics of spacecraft |
| CN107941441B (en) * | 2017-11-14 | 2019-12-03 | 北京卫星环境工程研究所 | Determine the method that in-orbit boundary influences the in-orbit kinetic characteristics of spacecraft of simulating |
| CN108573278A (en) * | 2018-03-14 | 2018-09-25 | 山东科技大学 | A kind of multiple operating modes process modal identification method |
| CN108573278B (en) * | 2018-03-14 | 2021-06-22 | 山东科技大学 | Multi-working-condition process modal identification method |
| CN108986436A (en) * | 2018-06-19 | 2018-12-11 | 上海卫星工程研究所 | A kind of communication system for the transmission of Satellite Vibration data |
| CN109632185A (en) * | 2018-12-13 | 2019-04-16 | 上海航天控制技术研究所 | A kind of in-orbit estimation method of large inertia rotatable parts unbalance dynamic characteristic |
| CN109612664A (en) * | 2019-01-08 | 2019-04-12 | 上海卫星工程研究所 | The in-orbit vibrational state method and system of satellite flexible appendage is recognized using gyro data |
| CN109655218A (en) * | 2019-01-08 | 2019-04-19 | 上海卫星工程研究所 | With the method and system of the whole star flexible vibration modal frequency of satellite gyroscope data identification |
| CN109917797A (en) * | 2019-01-09 | 2019-06-21 | 上海卫星工程研究所 | Utilize the whole star flexible vibration modal damping method and system of satellite gyroscope data identification |
| CN111177885A (en) * | 2019-12-09 | 2020-05-19 | 上海航天控制技术研究所 | Ground experiment method for dynamic characteristics of formation of large flexible spacecraft |
| CN111177885B (en) * | 2019-12-09 | 2023-09-12 | 上海航天控制技术研究所 | Ground experiment method for formation dynamics characteristics of large flexible spacecraft |
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Application publication date: 20160413 |