CN109612665A - Recognize the method and system of whole star flexible vibration modal parameter - Google Patents
Recognize the method and system of whole star flexible vibration modal parameter Download PDFInfo
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- CN109612665A CN109612665A CN201910017431.1A CN201910017431A CN109612665A CN 109612665 A CN109612665 A CN 109612665A CN 201910017431 A CN201910017431 A CN 201910017431A CN 109612665 A CN109612665 A CN 109612665A
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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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- 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 present invention provides a kind of methods for recognizing whole star flexible vibration modal parameter comprising the steps of: attitude angular velocity obtaining step: the corresponding attitude angular velocity measurement data ω of i axis in the underdamping free vibration area after obtaining the in-orbit jet closed-loop control of satellitei(t), wherein i axis is X-axis, Y-axis, any one axis in Z axis in rectangular coordinate system in space；Filter step: to ωi(t) it is filtered and obtains filtered i axis attitude angular velocity data ω 'i(t)；In-orbit vibration frequency calculates step: according to ω 'i(t) it calculates and obtains in-orbit vibration frequency fi；Time series calculates step: according to ω 'i(t) the time series η for obtaining mode variable is calculatedi(t)；Damping calculating step: according to the damping ξ for calculating acquisition i shaft vibration modei.The present invention meets the needs of in-orbit structural dynamic characteristics of flexible satellite recognize, and extracts the whole star flexible vibration modal parameter such as in-orbit flexible vibration modal frequency and damping ratios.
Description
Technical field
The present invention relates to flexible satellite Structural Dynamics fields, and in particular, to a kind of whole star flexible vibration mode of identification
The method and system of parameter, especially a kind of method using the whole star flexible vibration modal parameter of satellite gyroscope data identification be
System.More particularly to a kind of in-orbit identification method and system for the in-orbit mode of oscillation of flexible satellite, it is specifically a kind of right
The discrimination method and system of the structural dynamic parameters such as the in-orbit flexible vibration modal frequency of satellite and damping ratios.
Background technique
With the continuous development of space technology, large space structure has been an important development side in space industry
To also will being infrastructure [the in-orbit spacecraft dynamics parameter identification of Yu Dengyun, Xia Renwei, Sun Guojiang of space development indispensability
Technical research China's Space science and technology, 2 months 2008, the 1st phase].To obtain flexible satellite structural dynamic characteristics, Chang Cai
Vibrating modal parameters are calculated with the methods of finite element modeling, ground experiment and in-orbit identification.Model in finite element modeling process
Simplification, condition hypothesis etc. affect model accuracy, are especially difficult to the contacts such as hinge mechanism Accurate Model.Due to gravity and
The influence of the factors such as atmospheric drag, Large Flexible Structure are difficult that full-scale kinetic parameter is assembled and implemented on ground to distinguish
Know test.Therefore, for the spacecraft with large-scale flexible appendage, it is difficult to be obtained accurately by finite element modeling or ground experiment
Structural dynamic parameter.Based on above-mentioned factor, in-orbit mode ginseng is carried out to the big flexible structure such as sun battle array, space development antenna
Number Research on Identification are very urgent and necessary, while also theory significance with higher and practical application values.Flexible satellite
Structural dynamic parameter includes modal frequency, modal damping, formation, coefficient of coup etc., and there is these parameters important physics to anticipate
Justice can be the structure design of space flexible part, monitoring structural health conditions, structure failure diagnosis, structural vibration control etc.
Application necessary support [CN102982196A] is provided.As [CN103926840A] describes a kind of utilization ZVD former master
The dynamic method for inhibiting solar array flexible vibration, using to flexible mode damping ratio and modal frequency as mode input.
The Modal Parameters Identification in Structural Dynamics field mainly includes frequency domain method, time domain approach and in recent years at present
Three kinds of the time-frequency domain method of rise.Most methods are needed using in-orbit excitation and placement sensor obtains letter on flexible appendage
Breath, such as [Li Xiaoran large-sized solar windsurfing modal parameter in-orbit identification studies Harbin Institute of Technology master thesis,
In June, 2013] have studied the minimal configuration quantity and optimal location scheme of sensor on flexible appendage；[CN105486474A] is situated between
Continued a kind of satellite flexible part in-orbit modal identification realization system and method, need to flexible appendage carry out pulse swash
It encourages, receives and monitor the impulse response signal of each measuring point, and acquire the in-orbit steady state operation Satellite flexible part of satellite
Generated acceleration responsive signal；[CN106557633A] and [CN107609296A] describes satellite sun array sensor cloth
The two methods of office.The solar sail deployed configuration dynamic characteristic in-orbit identification side of [CN106408570A] based on Binocular vision photogrammetry
Method directly extracts structural vibration displacement information from image, and then obtains the dynamic of structure in real time by operational modal analysis technology
Step response realizes the in-orbit identification of Structure Dynamic Characteristics.Also two patents propose the attitude angular velocity number using gyro to measure
According to the in-orbit identification method to flexible satellite modal parameter: [CN103970964A] describes a kind of flexible satellite modal parameter and exists
Rail discrimination method needs to collect torque and flexible satellite body relative inertness coordinate that executing agency is applied on flexible satellite body
The angular velocity information of system obtains the transmission function of modal parameter with torque to angular speed using Subspace Identification algorithm.
[CN105157728A] proposes a kind of flexible satellite Modal Parameters Identification that can inhibit gyro noise influence, also with
The measurement data of satellite body angular speed recognizes the modal frequency and damping ratios parameter of whole star when satellite in-orbit flight, to top
Spiral shell data carry out difference processing and inhibit Identification Errors caused by this two parts noise.
There are two constraints in terms of engineer application for the above in-orbit dynamic parameters identification method of flexible satellite: first is that in-orbit boat
Its device is difficult to required for applying dynamic parameters identification known excitation, can only utilize the expansion and gathering of in-orbit space structure,
The docking and separation of structure, the igniting of engine etc. generate driving source and are motivated, and these excitation source signals are all difficult to measure
[the in-orbit spacecraft dynamics parameter identification technique research China's Space science and technology of Yu Dengyun, Xia Renwei, Sun Guojiang, 2008
2 months years, the 1st phase].Second is that the quantity for installing vibrating sensor on flexible appendage receives the limitation of engineering construction.It is general to scratch
Property attachment is required to in-orbit expansion, and all kinds of speed, accelerations, the installation fixation of displacement sensor, cable laying etc. are to expansion
Mechanism has an adverse effect, and increases design difficulty.In addition, also needing to increase driving machine for the rotational flexibilities component such as sun battle array
Structure slip ring signal number of channels.
Summary of the invention
For the defects in the prior art, whole star flexible vibration modal parameter is recognized the object of the present invention is to provide a kind of
Method and system.
The method of the whole star flexible vibration modal parameter of identification provided according to the present invention comprising the steps of:
Attitude angular velocity obtaining step: the i axis in the underdamping free vibration area after obtaining the in-orbit jet closed-loop control of satellite
Corresponding attitude angular velocity measurement data ωi(t), wherein i axis is X-axis, Y-axis, any in Z axis in rectangular coordinate system in space
A axis；
Filter step: to ωi(t) it is filtered and obtains filtered i axis attitude angular velocity data ωi′(t)；
In-orbit vibration frequency calculates step: according to ωi' (t), which is calculated, obtains in-orbit vibration frequency fi；
Time series calculates step: according to ωi' (t) calculates the time series η for obtaining mode variablei(t)；
Damping calculating step: according to the damping ξ for calculating acquisition i shaft vibration modei。
Preferably, in attitude angular velocity obtaining step, ωiIt (t) is that underdamping is freely shaken after the in-orbit gas puff Z-pinch of satellite
It in dynamic period, is obtained by satellite gyroscope measurement.
Preferably, the filter step comprises the steps of:
Concern vibration frequency band setting steps: the concern vibration frequency band of setting i axis direction is [f1,f2]Hz；
Strip step: enable bandpass filter to ωi(t) ω is removed in row filtering processingiIt (t) is more than the period of setting value in
Movement and high-frequency vibration component only retain the vibration information closed in vibration injection band, obtain ωi′(t)。
Preferably, in concern vibration frequency band setting steps, according to ground flexible satellite dynamic analysis calculated result,
The concern vibration frequency band of i axis direction is set.
Preferably, in-orbit vibration frequency calculates in step, to ωi' (t) carries out power spectral-density analysis, power spectral density
Frequency band [f is vibrated in concern1,f2] respective frequencies of maximum value form the in-orbit vibration frequency f of concern mode in the section Hzi。
Preferably, time series calculates step and comprises the steps of:
First derivative step of converting: according to the following formula to ωi' (t) is handled:
In formula:For the first derivative of the corresponding mode variable of i axis；
JiFor satellite i axis direction rotary inertia；
BiFor the rotation coefficient of coup of the corresponding flexible appendage mode of oscillation of i axis；
Integration step: rightIntegral calculation is carried out, η is obtainedi(t)。
Preferably, Damping calculating step comprises the steps of:
Characteristic extraction step: η is extractedi(t) vibration external envelope point yiAnd its corresponding time ti；
Fitting coefficient calculates step: using exponential functionTo yiWith tiIt is fitted, obtains fitting coefficient ai、bi；
Damping values obtaining step: ξ is calculated according to fitting coefficienti。
Preferably, ξ is calculated according to the following formulai:
The present invention also provides a kind of systems for recognizing whole star flexible vibration modal parameter, comprising with lower module:
Attitude angular velocity obtains module: the i axis in the underdamping free vibration area after obtaining the in-orbit jet closed-loop control of satellite
Corresponding attitude angular velocity measurement data ωi(t), wherein i axis is X-axis, Y-axis, any in Z axis in rectangular coordinate system in space
A axis；
Filter module: to ωi(t) it is filtered and obtains filtered i axis attitude angular velocity data ωi′(t)；
In-orbit vibration frequency calculates module: according to ωi' (t), which is calculated, obtains in-orbit vibration frequency fi；
Time series computing module: according to ωi' (t) calculates the time series η for obtaining mode variablei(t)；
Damping calculating module: according to the damping ξ for calculating acquisition i shaft vibration modei。
Preferably, it is obtained in module in attitude angular velocity, ωiIt (t) is that underdamping is freely shaken after the in-orbit gas puff Z-pinch of satellite
It in dynamic period, is obtained by satellite gyroscope measurement.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the present invention meets the needs of in-orbit structural dynamic characteristics of flexible satellite recognize, and extracts in-orbit flexible vibration mode
The whole star flexible vibration modal parameter such as frequency and damping ratios.
2, compared with other calculate the method for the in-orbit structural dynamic parameter of satellite, this method is not needed on flexible appendage
Other installation sensors, are analyzed and processed merely with the measurement data of the existing inertial attitude sensor of satellite platform.
3, increased design of satellites, manufacture difficulty and wind in orbit are avoided because installing other vibrating sensors
Danger.
4, the whole star flexible vibration modal parameter picked out can supervise for the structure design of space flexible part, structural health
The application of survey, structure failure diagnosis, structural vibration control etc. provides necessary support.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is certain single-blade sun battle array satellite configuration schematic diagram；
Fig. 2 is the attitude angular velocity change curve in satellite in-orbit jet closed-loop control period；
Fig. 3 is the time domain comparison diagram of measuring satellite angular velocities filtering front and back；
Fig. 4 is the frequency domain comparison diagram of measuring satellite angular velocities filtering front and back；
Fig. 5 is change curve and the external envelope fitting of flexible mode variable；
Fig. 6 is the method and step flow chart for recognizing whole star flexible vibration modal parameter.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
In the description of the present invention, it is to be understood that, term " on ", "lower", "front", "rear", "left", "right", " perpendicular
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, is merely for convenience of description of the present invention and simplification of the description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.
The method of the whole star flexible vibration modal parameter of identification provided by the invention comprising the steps of: attitude angular velocity obtains
Take step: the corresponding attitude angular velocity measurement of the i axis in the underdamping free vibration area after obtaining the in-orbit jet closed-loop control of satellite
Data ωi(t), wherein i axis is X-axis, Y-axis, any one axis in Z axis in rectangular coordinate system in space；Filter step: to ωi
(t) it is filtered and obtains filtered i axis attitude angular velocity data ωi′(t)；In-orbit vibration frequency calculates step: according to ωi′
(t) it calculates and obtains in-orbit vibration frequency fi；Time series calculates step: according to ωi' (t) calculates the time sequence for obtaining mode variable
Arrange ηi(t)；Damping calculating step: according to the damping ξ for calculating acquisition i shaft vibration modei.Wherein, in attitude angular velocity obtaining step
In, ωi(t) it is underdamping free vibration period after the in-orbit gas puff Z-pinch of satellite, is obtained by satellite gyroscope measurement.
The filter step comprises the steps of: concern vibration frequency band setting steps: the concern vibration frequency of setting i axis direction
Band is [f1,f2]Hz；Strip step: enable bandpass filter to ωi(t) ω is removed in row filtering processingiIt (t) is more than setting value in
Periodic motion and high-frequency vibration component, only retain close vibration injection band in vibration information, obtain ωi′(t).The concern
It vibrates in frequency band setting steps, according to ground flexible satellite dynamic analysis calculated result, frequency is vibrated in the concern that i axis direction is arranged
Band.In-orbit vibration frequency calculates in step, to ωi' (t) carries out power spectral-density analysis, and power spectral density is in concern vibration frequency
Band [f1,f2] respective frequencies of maximum value form the in-orbit vibration frequency f of concern mode in the section Hzi。
Time series calculates step and comprises the steps of: first derivative step of converting: according to the following formula to ωi' (t) into
Row processing:
In formula:For the first derivative of the corresponding mode variable of i axis；JiFor satellite i axis direction rotary inertia；Bi
For the rotation coefficient of coup of the corresponding flexible appendage mode of oscillation of i axis；Integration step: rightIntegral calculation is carried out, η is obtainedi
(t)。
Damping calculating step comprises the steps of: characteristic extraction step: extracting ηi(t) vibration external envelope point yiAnd its
Corresponding time ti；Fitting coefficient calculates step: using exponential functionTo yiWith tiIt is fitted, obtains fitting coefficient
ai、bi；Damping values obtaining step: ξ is calculated according to fitting coefficienti.Preferably, ξ is calculated according to the following formulai:
Correspondingly, the present invention also provides a kind of systems for recognizing whole star flexible vibration modal parameter, comprising with lower module:
Attitude angular velocity obtains module: the corresponding appearance of i axis in the underdamping free vibration area after obtaining the in-orbit jet closed-loop control of satellite
State angular velocity measurement data ωi(t), wherein i axis is X-axis, Y-axis, any one axis in Z axis in rectangular coordinate system in space；Filter
Wave module: to ωi(t) it is filtered and obtains filtered i axis attitude angular velocity data ωi′(t)；In-orbit vibration frequency calculates mould
Block: according to ωi' (t), which is calculated, obtains in-orbit vibration frequency fi；Time series computing module: according to ωi' (t), which is calculated, obtains mode
The time series η of variablei(t)；Damping calculating module: according to the damping ξ for calculating acquisition i shaft vibration modei.Wherein, in attitude angle
In speed acquiring module, ωi(t) it is underdamping free vibration period after the in-orbit gas puff Z-pinch of satellite, is measured by satellite gyroscope
It obtains.
The filter module includes with lower module: concern vibration frequency band setup module: frequency is vibrated in the concern of setting i axis direction
Band is [f1,f2]Hz；Strip module: enable bandpass filter to ωi(t) ω is removed in row filtering processingiIt (t) is more than setting value in
Periodic motion and high-frequency vibration component, only retain close vibration injection band in vibration information, obtain ωi′(t).The concern
It vibrates in frequency band setup module, according to ground flexible satellite dynamic analysis calculated result, frequency is vibrated in the concern that i axis direction is arranged
Band.In-orbit vibration frequency calculates in module, to ωi' (t) carries out power spectral-density analysis, and power spectral density is in concern vibration frequency
Band [f1,f2] respective frequencies of maximum value form the in-orbit vibration frequency f of concern mode in the section Hzi。
Time series computing module includes with lower module: first derivative conversion module: according to the following formula to ωi' (t) into
Row processing:
In formula:For the first derivative of the corresponding mode variable of i axis；JiFor satellite i axis direction rotary inertia；Bi
For the rotation coefficient of coup of the corresponding flexible appendage mode of oscillation of i axis；Integration module: rightIntegral calculation is carried out, η is obtainedi
(t)。
Damping calculating module includes with lower module: characteristic extracting module: extracting ηi(t) vibration external envelope point yiAnd its
Corresponding time ti；Fitting coefficient computing module: exponential function is usedTo yiWith tiIt is fitted, obtains fitting coefficient
ai、bi；Damping values obtain module: ξ is calculated according to fitting coefficienti.Preferably, ξ is calculated according to the following formulai:
Preferred embodiment:
Certain remote sensing satellite is equipped with single-blade solar battery array, and configuration is shown in Fig. 1.After transmitting is entered the orbit, during gas puff Z-pinch
It is as shown in Figure 2 to roll X-axis attitude angular velocity measurement data.
Step 1: the rolling X-axis attitude angular velocity in the underdamping free vibration area after choosing the in-orbit jet closed-loop control of satellite
Measurement data ωX(t) (Fig. 2) is analyzed.
Step 2: according to ground flexible satellite dynamic analysis calculated result, the frequency of X-direction principal oscillation mode is about
0.37Hz, the vibration frequency band that concern is arranged is [0.259,0.481] Hz, using the fertile hereby bandpass filter of 5 rank Barts to underdamping
Free vibration area attitude angular velocity measurement data ωX(t) it is filtered, removing rolls in X-axis attitude angular velocity signal
The phugoid mode of motion and high-frequency vibration component only retain the vibration information in concern frequency band, obtain filtered rolling X-axis attitude angle
Speed omegaX′(t)。
Fig. 3 and Fig. 4 are shown in the time domain comparison and power spectral density comparison of attitude angular velocity measurement data filtering front and back respectively.From
Time domain comparison and frequency domain comparison can be clearly seen, and the signal within [0.259,0.481] Hz frequency band is retained, remaining frequency range
Signal is substantially weakened.
Step 3: to rolling X-axis attitude angular velocity ω after filteringX' (t) carries out power spectral-density analysis, and power spectral density exists
The respective frequencies of maximum value are to pay close attention to the in-orbit vibration frequency f of mode in the section [0.259,0.481] HzX.As can be seen from Figure 4, fX
=0.36621Hz.
Step 4: according to formulaBy filtered single-axis attitude angular velocity omegaX' (t) is converted into mode
The first derivative of variableWherein, JX=6872.13kgm2It is satellite in the rotary inertia for rolling X-direction, BX=
33.48762m·kg1/2For the rotation coefficient of coup of flexible appendage mode of oscillation.Again to the first derivative of mode variableInto
Row integral, obtains the time series η of mode variableX(t), see Fig. 5.
Step 5: extracting mode variable ηX(t) vibration external envelope point yXAnd its corresponding time tX, use exponential functionExternal envelope is vibrated to it and is fitted (Fig. 5), obtains fitting coefficient aX、bX.According to formulaRolling can be calculated
The damping ratio of dynamic X axis vibration mode.In this example, fitting coefficient result are as follows: aX=3.375 × 1021、bX=-0.009565, meter
The damping ratio result of calculating are as follows: ξX=0.001522.
One skilled in the art will appreciate that in addition to realizing system provided by the invention in a manner of pure computer readable program code
It, completely can be by the way that method and step be carried out programming in logic come so that provided by the invention other than system, device and its modules
System, device and its modules are declined with logic gate, switch, specific integrated circuit, programmable logic controller (PLC) and insertion
The form of controller etc. realizes identical program.So system provided by the invention, device and its modules may be considered that
It is a kind of hardware component, and the knot that the module for realizing various programs for including in it can also be considered as in hardware component
Structure；It can also will be considered as realizing the module of various functions either the software program of implementation method can be Hardware Subdivision again
Structure in part.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of method for recognizing whole star flexible vibration modal parameter, which is characterized in that comprise the steps of:
Attitude angular velocity obtaining step: the i axis in the underdamping free vibration area after obtaining the in-orbit jet closed-loop control of satellite is corresponding
Attitude angular velocity measurement data ωi(t), wherein i axis is X-axis, Y-axis, any of Z axis in rectangular coordinate system in space
Axis；
Filter step: to ωi(t) it is filtered and obtains filtered i axis attitude angular velocity data ω 'i(t)；
In-orbit vibration frequency calculates step: according to ω 'i(t) it calculates and obtains in-orbit vibration frequency fi；
Time series calculates step: according to ω 'i(t) the time series η for obtaining mode variable is calculatedi(t)；
Damping calculating step: according to the damping ξ for calculating acquisition i shaft vibration modei。
2. the method for the whole star flexible vibration modal parameter of identification according to claim 1, which is characterized in that in attitude angle speed
It spends in obtaining step, ωi(t) it is underdamping free vibration period after the in-orbit gas puff Z-pinch of satellite, is measured by satellite gyroscope
It arrives.
3. the method for the whole star flexible vibration modal parameter of identification according to claim 1, which is characterized in that the filtering step
Suddenly it comprises the steps of:
Concern vibration frequency band setting steps: the concern vibration frequency band of setting i axis direction is [f1,f2]Hz；
Strip step: enable bandpass filter to ωi(t) ω is removed in row filtering processingiIt (t) is more than the periodic motion of setting value in
With high-frequency vibration component, only retains the vibration information closed in vibration injection band, obtain ω 'i(t)。
4. the method for the whole star flexible vibration modal parameter of identification according to claim 3, which is characterized in that the concern vibration
In dynamic frequency band setting steps, according to ground flexible satellite dynamic analysis calculated result, frequency is vibrated in the concern that i axis direction is arranged
Band.
5. the method for the whole star flexible vibration modal parameter of identification according to claim 3, which is characterized in that in-orbit vibration frequency
Rate calculates in step, to ω 'i(t) power spectral-density analysis is carried out, power spectral density vibrates frequency band [f in concern1,f2] section Hz
The respective frequencies of interior maximum value form the in-orbit vibration frequency f of concern modei。
6. the method for the whole star flexible vibration modal parameter of identification according to claim 1, which is characterized in that time series meter
Step is calculated to comprise the steps of:
First derivative step of converting: according to the following formula to ω 'i(t) it is handled:
In formula:For the first derivative of the corresponding mode variable of i axis；
JiFor satellite i axis direction rotary inertia；
BiFor the rotation coefficient of coup of the corresponding flexible appendage mode of oscillation of i axis；
Integration step: rightIntegral calculation is carried out, η is obtainedi(t)。
7. the method for the whole star flexible vibration modal parameter of identification according to claim 1, which is characterized in that Damping calculating step
Suddenly it comprises the steps of:
Characteristic extraction step: η is extractedi(t) vibration external envelope point yiAnd its corresponding time ti；
Fitting coefficient calculates step: using exponential functionTo yiWith tiIt is fitted, obtains fitting coefficient ai、bi；
Damping values obtaining step: ξ is calculated according to fitting coefficienti。
8. the method for the whole star flexible vibration modal parameter of identification according to claim 7, which is characterized in that according to following public affairs
ξ is calculated in formulai:
9. a kind of system for recognizing whole star flexible vibration modal parameter, which is characterized in that comprising with lower module:
Attitude angular velocity obtains module: the i axis in the underdamping free vibration area after obtaining the in-orbit jet closed-loop control of satellite is corresponding
Attitude angular velocity measurement data ωi(t), wherein i axis is X-axis, Y-axis, any of Z axis in rectangular coordinate system in space
Axis；
Filter module: to ωi(t) it is filtered and obtains filtered i axis attitude angular velocity data ω 'i(t)；
In-orbit vibration frequency calculates module: according to ω 'i(t) it calculates and obtains in-orbit vibration frequency fi；
Time series computing module: according to ω 'i(t) the time series η for obtaining mode variable is calculatedi(t)；
Damping calculating module: according to the damping ξ for calculating acquisition i shaft vibration modei。
10. the system of the whole star flexible vibration modal parameter of identification according to claim 9, which is characterized in that in attitude angle
In speed acquiring module, ωi(t) it is underdamping free vibration period after the in-orbit gas puff Z-pinch of satellite, is measured by satellite gyroscope
It obtains.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110929386A (en) * | 2019-11-01 | 2020-03-27 | 上海卫星工程研究所 | Method for identifying whole satellite flexible vibration modal parameters by using satellite gyroscope data |
| CN113359431A (en) * | 2021-06-17 | 2021-09-07 | 北京控制工程研究所 | Online identification and inhibition method for spacecraft flexible vibration |
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