CN106596005A - Active recessed mechanical condition making module in vibration control system - Google Patents
Active recessed mechanical condition making module in vibration control system Download PDFInfo
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- CN106596005A CN106596005A CN201610559815.2A CN201610559815A CN106596005A CN 106596005 A CN106596005 A CN 106596005A CN 201610559815 A CN201610559815 A CN 201610559815A CN 106596005 A CN106596005 A CN 106596005A
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- G—PHYSICS
- G01—MEASURING; TESTING
- 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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- G—PHYSICS
- G01—MEASURING; TESTING
- 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
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D19/00—Control of mechanical oscillations, e.g. of amplitude, of frequency, of phase
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Vibration Prevention Devices (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses an active recessed mechanical condition making module in a vibration control system. The module includes six sub-modules: (1) a low-level test condition input sub-module; (2) a response amplitude limit point low-level measurement data import sub-module; (3) a high-level test condition input sub-module; (4) a response amplitude limit condition input sub-module; (5) a high-level active recessed condition making sub-module; and (6) a recessed condition display and storage sub-module; wherein the response amplitude limit condition of each response amplitude limit point is input, and the test conditions include amplitude limit frequency range and amplitude limit test magnitude; and the high-level active recessed condition making sub-module successively predicts the response of each response test point under the high-level test condition based on the input information of the (1) to (4) modules according to the linear relation. The making of the active recessed mechanic conditions is fused into a vibration control system, the independent modules of the vibration control system can complete the work to get rid of the defects that the previous condition making excessively depends on the experience of test personnel and massive calculation can be carried out; and meanwhile, the vibration control system can conveniently perform automatic calling of the made recessed conditions, so that the spacecraft mechanical environment testing efficiency can be greatly improved.
Description
Technical field
The invention belongs to spacecraft dynamic environmental test field, and in particular to the recessed power of active in a kind of vibration control system
Condition formulates module.
Background technology
Vibration control system is a very important ingredient in spacecraft dynamic environmental test, and it is by measuring boat
Response at its device product inputting interface, and be compared with reference test condition, amendment in real time inputs to power amplifier
Drive signal, it is ensured that the response at spacecraft inputting interface control point is consistent with reference test condition.
Vibration control system typically all possesses passive response amplitude limit control function.The function is as in advance in the controls
The amplitude limit magnitude of certain monitoring point on spacecraft product is set, if the response of the clipping point is less than the amplitude limit for arranging during test is carried out
Magnitude, then control system tested by reference test condition；If the response of the clipping point is controlled more than the amplitude limit magnitude for arranging
System processed carries out automatically recessed, responding less than the amplitude limit magnitude for arranging up to clipping point to the magnitude of inputting interface.
For on spacecraft, some dampings of local are little, the measuring point of peak value of response point, passive response amplitude limit control function is not
Preferable effect can be obtained, is carried out general with the actively recessed mode of mechanical condition.The system of current actively recessed mechanical condition
The recessed mechanical condition of active fixed generally to be completed by manually computing by experienced technical staff, that subsequently formulation is completed
Input to vibration control system；Or foundation《Forecasting system for high-magnitude test condition of sinusoidal vibration test for spacecraft》(grant number
For ZL201110406703.0) method described in patent is by the computed in software independent with the incoherent outside of vibration control system
Go out the recessed condition of high-magnitude, subsequent testing crew carries out mechanical test to vibration control system according to the condition entry, but this is special
Profit is only limited to sinusoidal experiments.《Method is determined based on the spacecraft control of product envelope of vibration rig ability》(number of accepting is
201610124270.2) describe to lead the input condition of spacecraft product according to the ability of vibration rig in patent
Dynamic recessed, the method can give full play to the thrust capacity of vibration rig, can ensure that spacecraft product in process of the test again
In do not occur interrupt, make product undergo to greatest extent dynamic environmental test examination.
The formulation of above two active recessed mechanical condition is incorporated vibration control system by the present invention, and be increased with owner
Dynamic recessed mechanical condition formulates function, and the work is completed by the single module of vibration control system.Own in the market
Vibration control system without this functional module, the module can facilitate the formulation of experimental condition and vibration control system to test bar
Part is efficiently called, it is ensured that the safety of spacecraft product, greatly improves spacecraft dynamic environmental test efficiency.
The content of the invention
It is an object of the invention to provide actively recessed mechanical condition formulates module in vibration control system, the module is according to low
Magnitude experimental condition, response amplitude limit measuring point low amounts level test data, response amplitude limit condition are formulating high-magnitude actively recessed mechanics
Condition, the condition are available for vibration control system to call automatically and as the input of mechanical test.The module can facilitate experimental condition
Formulation, improve test efficiency.
The present invention is realized by the following technical solutions：
In vibration control system, actively recessed mechanical condition formulates module, mainly includes six submodules：
(1) low amounts level experimental condition input submodule, the input test bar of the completed low magnitude vibration test of its input
Part, experimental condition include vibration frequency range and loading magnitude；
(2) respond clipping point low amounts level measurement data and import submodule, its each measuring point of input is after the completion of the test of low amounts level
Test data, data demand be UFF (general data file) form；
(3) high-magnitude experimental condition input submodule, its input high-magnitude experimental condition, experimental condition include frequency of vibration
Scope and loading magnitude；
(4) amplitude limit condition entry submodule is responded, the response amplitude limit condition of each response clipping point of its input, experimental condition bag
Include amplitude limit frequency range and amplitude limit test magnitude；
(5) actively recessed condition formulates submodule to high-magnitude, and which presses linear pass according to the input information of (1) to (4) step
System predicts each response response of the measuring point under high-magnitude experimental condition successively, if the response level exceedes response amplitude limit condition
In amplitude limit magnitude, then experimental condition carry out recessed process, vibration control system is taken to the recessed conditions of all response clipping points
Lower envelope, the recessed condition of high-magnitude active that the envelope is as formulated；
(6) recessed condition shows and sub-module stored which carries out amplitude-frequency to the recessed condition of high-magnitude active formulated and shows,
And stored with the form of UFF, called for vibration control system automatically；
Wherein in step (5), the high-magnitude detailed process that actively recessed condition is formulated is as follows：
If low magnitude vibration experimental condition is a (f), test measurement data are aiF () (i is measuring point number, if n survey
Point, then i=1,2 ..., n).The measurement not only includes the measurement of response point on spacecraft product, also including in vibration experiment
The measurement of power amplifier output current.High-magnitude experimental condition is A (f).According to the test data that formula (1) can estimate high-magnitude it is
Ai(f)。
Compare the prediction experiment data and response amplitude limit condition of each measuring point, if response value exceedes in response amplitude limit condition
Amplitude limit tests magnitude, then need to be adjusted high-magnitude experimental condition.
If the response data of prediction high-magnitude is AiF (), given response amplitude limit are tested magnitude and areThen with the survey
Revised high-magnitude condition A of the corresponding adjustment of point amplitude limit conditioni' (f) can be predicted by formula (2).
It is possible thereby to obtain a series of revised high-magnitude conditions Ai' (f), the lower envelope of comprehensive each response clipping point are bent
Line obtains high-magnitude actively recessed condition.
The formulation of the recessed condition of high-magnitude active will come comprehensive with reference to the current signals of all response amplitude limit measuring points and power amplifier
Formulate recessed condition.
In vibration control system, actively recessed mechanical condition formulates module registration string and random experiment is suitable for.
The present invention has taken into full account that actively recessed mechanical condition formulates the required link for considering to spacecraft, breaks away from system in the past
Fixed condition too relies on the experience of testing crew, and needs the drawbacks of being calculated in a large number；Facilitate vibration control system simultaneously
Recessed condition to formulating is called automatically, improves test efficiency.
Description of the drawings
Fig. 1 is the recessed mechanical condition formulation function structure chart of active in vibration control system of the invention.
Specific embodiment
In 1 pair of vibration control system of the invention, actively recessed mechanical condition formulates module work further below in conjunction with the accompanying drawings
Explanation.
As shown in figure 1, actively recessed mechanical condition formulation module includes six submodules in the vibration control system of the present invention
Block：(1) low amounts level experimental condition input submodule；(2) respond clipping point low amounts level measurement data and import submodule；(3) a large amount
Level experimental condition input submodule；(4) respond amplitude limit condition entry submodule；(5) actively recessed condition formulates submodule to high-magnitude
Block；(6) recessed condition shows and sub-module stored, wherein, low amounts level experimental condition input submodule is that input is completed low
The input experimental condition of magnitude vibration test, experimental condition include vibration frequency range and loading magnitude；Response clipping point low amounts
Level measurement data imports submodule, its test data of each measuring point of input after the completion of the test of low amounts level, and data demand is UFF lattice
Formula；High-magnitude experimental condition input submodule, its input high-magnitude experimental condition, experimental condition include vibration frequency range and add
Carrying capacity level；Response amplitude limit condition entry submodule, the response amplitude limit condition of each response clipping point of its input, experimental condition include limit
Swing frequency scope and amplitude limit test magnitude；Actively recessed condition formulates submodule to high-magnitude, and which is defeated according to (1) to (4) module
Enter information and each response response of the measuring point under high-magnitude experimental condition is predicted successively by linear relationship, if the response level is super
The amplitude limit magnitude responded in amplitude limit condition is crossed, then experimental condition carries out recessed process.Vibration control system is to all response amplitude limits
The recessed condition of point removes envelope, the recessed condition of high-magnitude active that the envelope is as formulated；Recessed experimental condition shows and deposits
Storage submodule, which carries out amplitude-frequency to the recessed condition of high-magnitude active formulated and shows, and is stored with the form of UFF, for shaking
Autocontrol system is called automatically.
The wherein high-magnitude detailed process that actively recessed condition is formulated is as follows：
If low magnitude vibration experimental condition is a (f), test measurement data are aiF () (i is measuring point number, if n survey
Point, then i=1,2 ..., n).The measurement not only includes the measurement of response point on spacecraft product, also including in vibration experiment
The measurement of power amplifier output current.High-magnitude experimental condition is A (f).According to the test data that formula (1) can estimate high-magnitude it is
Ai(f)。
Compare the prediction experiment data and response amplitude limit condition of each measuring point, if response value exceedes in response amplitude limit condition
Amplitude limit tests magnitude, then need to be adjusted high-magnitude experimental condition.
If the response data of prediction high-magnitude is AiF (), given response amplitude limit are tested magnitude and areThen with the survey
Revised high-magnitude condition A of the corresponding adjustment of point amplitude limit conditioni' (f) can be predicted by formula (2).
It is possible thereby to obtain a series of revised high-magnitude conditions Ai' (f), the lower envelope of comprehensive each response clipping point are bent
Line obtains high-magnitude actively recessed condition.
In vibration control system, actively recessed mechanical condition formulation module not only considers amplitude limit measuring point is responded on spacecraft, together
When the whole capability of vibration experiment is taken into account.The formulation of the recessed condition of high-magnitude active will be with reference to all response amplitude limits
The current signal of measuring point and power amplifier comprehensively formulates recessed condition.In vibration control system, actively recessed mechanical condition formulates module
Sinusoidal and random experiment is suitable for.
The present invention has taken into full account that actively recessed mechanical condition formulates the required link for considering to spacecraft, breaks away from system in the past
Fixed condition too relies on the experience of testing crew, and needs the drawbacks of being calculated in a large number；Facilitate vibration control system simultaneously
Recessed condition to formulating is called automatically, improves test efficiency.
Although giving detailed description above to the specific embodiment of the present invention and illustrating, it should be noted that
We can carry out various equivalent changes and modification according to the conception of the present invention to above-mentioned embodiment, and the function produced by which is made
With still without departing from description and accompanying drawing covered it is spiritual when, all should be within protection scope of the present invention.
Claims (5)
1. in a kind of vibration control system, actively recessed mechanical condition formulates module, mainly includes six submodules：
(1) low amounts level experimental condition input submodule, the input experimental condition of the completed low magnitude vibration test of its input, examination
The condition of testing includes vibration frequency range and loading magnitude；
(2) respond clipping point low amounts level measurement data and import submodule, its examination of each measuring point of input after the completion of the test of low amounts level
Data are tested, data demand is UFF (general data file) form；
(3) high-magnitude experimental condition input submodule, its input high-magnitude experimental condition, experimental condition include vibration frequency range
With loading magnitude；
(4) amplitude limit condition entry submodule is responded, the response amplitude limit condition of each response clipping point of its input, experimental condition include limit
Swing frequency scope and amplitude limit test magnitude；
(5) actively recessed condition formulates submodule to high-magnitude, its according to the input information of (1) to (4) step press linear relationship according to
Secondary prediction is each to respond response of the measuring point under high-magnitude experimental condition, if the response level exceedes in response amplitude limit condition
Amplitude limit magnitude, then experimental condition carry out recessed process, vibration control system removes bag to the recessed conditions of all response clipping points
Network, the recessed condition of high-magnitude active that the envelope is as formulated；
(6) recessed condition shows and sub-module stored which carries out amplitude-frequency to the recessed condition of high-magnitude active formulated and shows, and with
The form of UFF is stored, and is called for vibration control system automatically；
Wherein in step (5), the high-magnitude detailed process that actively recessed condition is formulated is as follows：
If low magnitude vibration experimental condition is a (f), test measurement data are ai(f) (i is measuring point number, if n measuring point, then i
=1,2 ..., n), the measurement not only includes the measurement of response point on spacecraft product, also defeated including power amplifier in vibration experiment
Go out the measurement of electric current；High-magnitude experimental condition is A (f), and the test data that can estimate high-magnitude according to formula (1) is Ai(f),
Compare the prediction experiment data and response amplitude limit condition of each measuring point, if response value exceedes amplitude limit in response amplitude limit condition
Test magnitude, then need to be adjusted high-magnitude experimental condition；
If the response data of prediction high-magnitude is AiF (), given response amplitude limit are tested magnitude and areThen with the measuring point amplitude limit
Revised high-magnitude condition A of the corresponding adjustment of conditioni' (f) can be predicted by formula (2),
It is possible thereby to obtain a series of revised high-magnitude condition A 'iF (), the lower enveloping curve of comprehensive each response clipping point obtain
To the recessed condition of high-magnitude active.
2. in vibration control system as claimed in claim 1, actively recessed mechanical condition formulates module, it is characterised in that response
Amplitude limit is except considering the crucial measuring point on spacecraft product, while the power amplifier electric current for weighing vibration experiment thrust capacity is examined
Including considering.
3. in vibration control system as claimed in claim 1, actively recessed mechanical condition formulates module, it is characterised in that vibration
In control system, actively recessed mechanical condition formulates module registration string and random experiment is suitable for.
4. in vibration control system as claimed in claim 1, actively recessed mechanical condition formulates module, it is characterised in that actively
The formulation of recessed mechanical condition includes sinusoidal and random two classes test.
5. in vibration control system as claimed in claim 1, actively recessed mechanical condition formulates module, it is characterised in that align
For string test, its experimental condition is change curve of the acceleration amplitude with frequency；For random experiment, its experimental condition is
Change curve of the acceleration power spectral density value with frequency.
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| CN201610559815.2A CN106596005B (en) | 2016-07-15 | 2016-07-15 | Actively recessed mechanical condition formulates module in vibration control system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109000868A (en) * | 2018-05-07 | 2018-12-14 | 北京空间飞行器总体设计部 | A kind of recessed condition formulating method of spacecraft sine vibration test |
| CN110186632A (en) * | 2019-05-22 | 2019-08-30 | 航天科工空间工程发展有限公司 | A kind of vibration testing method of the basic excitation vibration condition recessed based on triangle |
| CN111595542A (en) * | 2020-05-18 | 2020-08-28 | 北京卫星环境工程研究所 | Spacecraft dynamics test data analysis system |
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| CN102539097A (en) * | 2011-12-09 | 2012-07-04 | 北京卫星环境工程研究所 | Forecasting system for high-magnitude test condition of sinusoidal vibration test for spacecraft |
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| CN103743535A (en) * | 2013-12-16 | 2014-04-23 | 中国科学院力学研究所 | Large-amplitude translation/rotation-coupled vibration experiment device loaded under the control of force and torque |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109000868A (en) * | 2018-05-07 | 2018-12-14 | 北京空间飞行器总体设计部 | A kind of recessed condition formulating method of spacecraft sine vibration test |
| CN110186632A (en) * | 2019-05-22 | 2019-08-30 | 航天科工空间工程发展有限公司 | A kind of vibration testing method of the basic excitation vibration condition recessed based on triangle |
| CN110186632B (en) * | 2019-05-22 | 2020-11-20 | 航天科工空间工程发展有限公司 | Vibration test method based on triangular concave basic excitation vibration condition |
| CN111595542A (en) * | 2020-05-18 | 2020-08-28 | 北京卫星环境工程研究所 | Spacecraft dynamics test data analysis system |
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| CN106596005B (en) | 2019-07-16 |
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