CN106596005B - Actively recessed mechanical condition formulates module in vibration control system - Google Patents
Actively recessed mechanical condition formulates module in vibration control system Download PDFInfo
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- CN106596005B CN106596005B CN201610559815.2A CN201610559815A CN106596005B CN 106596005 B CN106596005 B CN 106596005B CN 201610559815 A CN201610559815 A CN 201610559815A CN 106596005 B CN106596005 B CN 106596005B
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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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- General Physics & Mathematics (AREA)
- 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 actively recessed mechanical condition formulates module, including six submodules: (1) low amounts grade experimental condition input submodule in a kind of vibration control system；(2) response clipping point low amounts grade measurement data imports submodule；(3) high-magnitude experimental condition input submodule；(4) clipping condition entry submodule is responded；(5) actively recessed condition formulates submodule to high-magnitude；(6) recessed condition is shown and sub-module stored, wherein the response clipping condition of each response clipping point of input, experimental condition include clipping frequency range and clipping test magnitude；Actively recessed condition formulates submodule to high-magnitude, and response of each response measuring point under high-magnitude experimental condition is successively predicted by linear relationship according to the input information of (1) to (4) module.The formulation of the recessed mechanical condition of active is incorporated vibration control system by the present invention, this work is completed by the individual module of vibration control system, gets rid of the drawbacks of previous formulation condition excessively relies on the experience of testing crew and largely calculated；It facilitates vibration control system simultaneously to call the recessed condition of formulation automatically, greatly improves spacecraft dynamic environmental test efficiency.
Description
Technical field
The invention belongs to spacecraft dynamic environmental test fields, and in particular to actively recessed power in a kind of vibration control system
Condition formulates module.
Background technique
Vibration control system is a very important component part in spacecraft dynamic environmental test, it passes through measurement boat
Response at its device product input interface, and be compared with reference test condition, amendment inputs to power amplifier in real time
Driving signal, it is ensured that the response at spacecraft input interface control point is consistent with reference test condition.
Vibration control system generally all has by dynamic response clipping control function.The function is to shift to an earlier date in the controls
The clipping magnitude of certain monitoring point on spacecraft product is set, if the response of the clipping point is lower than the clipping being arranged during test carries out
Magnitude, then control system is tested by reference test condition；If the response of the clipping point is more than the clipping magnitude of setting, control
System processed is automatic recessed to the magnitude progress of input interface, until the response of clipping point is lower than the clipping magnitude being arranged.
For small, the measuring point of peak value of response point of the certain dampings in part on spacecraft, not by dynamic response clipping control function
Ideal effect can be obtained, is carried out general with the recessed mode of mechanical condition active.The system of the recessed mechanical condition of active at present
It is fixed usually to be completed by experienced technical staff by manually computing, it will then formulate the recessed mechanical condition of active completed
Input to vibration control system；Or according to " forecasting system for high-magnitude test condition of sinusoidal vibration test for spacecraft " (grant number
It is method described in ZL201110406703.0) patent by being calculated with the independent software in the incoherent outside of vibration control system
The recessed condition of high-magnitude out, subsequent testing crew carries out mechanical test to vibration control system according to the condition entry, but this is specially
Benefit is only limited to sinusoidal experiments." determining method based on the spacecraft control of product envelope of vibration rig ability " (number of accepting is
201610124270.2) it describes in patent and the input condition of spacecraft product is led according to the ability of vibration rig
Move recessed, the thrust capacity and spacecraft product that this method can give full play to vibration rig are in test process
In do not interrupt, so that product is subjected to the examination of maximum dynamic environmental test.
The formulation of the recessed mechanical condition of above two active is incorporated vibration control system by the present invention, and is increased with owner
It moves recessed mechanical condition and formulates function, this work is completed by the individual module of vibration control system.Own currently on the market
The vibration control system formulation that can facilitate experimental condition without this functional module, the module and vibration control system to test bar
The efficient calling of part, ensure that the safety of spacecraft product, greatly improve spacecraft dynamic environmental test efficiency.
Summary of the invention
The object of the present invention is to provide the recessed mechanical conditions of active in vibration control system to formulate module, and the module is according to low
Magnitude experimental condition, response clipping measuring point low amounts grade test data respond clipping condition to formulate high-magnitude actively recessed mechanics
Condition, which calls automatically for vibration control system and the input as mechanical test.The module can facilitate experimental condition
Formulation, improve test efficiency.
The present invention realizes by the following technical solutions:
Actively recessed mechanical condition formulates module in vibration control system, mainly includes six submodules:
(1) low amounts grade experimental condition input submodule inputs the input test bar of completed low magnitude vibration test
Part, experimental condition include vibration frequency range and load magnitude；
(2) response clipping point low amounts grade measurement data imports submodule, inputs each measuring point after the completion of low amounts grade is tested
Test data, data demand be UFF (general data file) format；
(3) high-magnitude experimental condition input submodule inputs high-magnitude experimental condition, and experimental condition includes vibration frequency
Range and load magnitude；
(4) clipping condition entry submodule is responded, the response clipping condition of each response clipping point, experimental condition packet are inputted
Include clipping frequency range and clipping test magnitude；
(5) actively recessed condition formulates submodule to high-magnitude, is closed according to the input information of (1) to (4) step by linear
System successively predicts response of each response measuring point under high-magnitude experimental condition, if the response level is more than response clipping condition
In clipping magnitude, then experimental condition carries out recessed processing, and vibration control system takes the recessed conditions of all response clipping points
Lower envelope, the envelope are the recessed condition of high-magnitude active formulated；
(6) recessed condition is shown and sub-module stored, and to the high-magnitude of formulation, actively recessed condition carries out amplitude-frequency and shows,
And stored with the format of UFF, it is called automatically for vibration control system；
Wherein the high-magnitude detailed process that actively recessed condition is formulated is as follows in step (5):
If low magnitude vibration experimental condition is a (f), test measurement data are ai(f) (i is measuring point number, if there is n survey
Point, then i=1,2 ..., n).The measurement not only includes the measurement of response point on spacecraft product, also includes in vibration experiment
The measurement of power amplifier output electric current.High-magnitude experimental condition is A (f).It is according to the test data that formula (1) can estimate high-magnitude
Ai(f)。
The prediction experiment data and response clipping condition for comparing each measuring point, if response is more than in response clipping condition
Clipping tests magnitude, then needs to be adjusted high-magnitude experimental condition.
If predicting that the response data of high-magnitude is Ai(f), given response clipping test magnitude isThen with the survey
The corresponding revised high-magnitude condition A of adjustment of point clipping conditioni' (f) can be predicted by formula (2).
It is possible thereby to obtain a series of revised high-magnitude condition AiThe lower envelope of ' (f), comprehensive each response clipping point are bent
Line obtains high-magnitude actively recessed condition.
The formulation of the recessed condition of high-magnitude active integrates the current signals in conjunction with all response clipping measuring points and power amplifier
Formulate recessed condition.
Actively recessed mechanical condition formulation module registration string and random experiment are applicable in vibration control system.
The present invention has fully considered that actively recessed mechanical condition formulates the required link considered to spacecraft, gets rid of previous system
Fixed condition excessively relies on the experience of testing crew, and needs the drawbacks of largely being calculated；Vibration control system is facilitated simultaneously
The recessed condition of formulation is called automatically, improves test efficiency.
Detailed description of the invention
Fig. 1 is that actively recessed mechanical condition formulates function structure chart in vibration control system of the invention.
Specific embodiment
Actively recessed mechanical condition formulates module work further in 1 pair of vibration control system of the invention with reference to the accompanying drawing
Explanation.
As shown in Figure 1, it includes six submodules that actively recessed mechanical condition, which formulates module, in vibration control system of the invention
Block: (1) low amounts grade experimental condition input submodule；(2) response clipping point low amounts grade measurement data imports submodule；(3) a large amount
Grade experimental condition input submodule；(4) clipping condition entry submodule is responded；(5) actively recessed condition formulates submodule to high-magnitude
Block；(6) recessed condition is shown and sub-module stored, wherein low amounts grade experimental condition input submodule is completed low to input
The input experimental condition of magnitude vibration test, experimental condition include vibration frequency range and load magnitude；Respond clipping point low amounts
Grade measurement data imports submodule, inputs test data of each measuring point after the completion of the test of low amounts grade, data demand is UFF lattice
Formula；High-magnitude experimental condition input submodule, inputs high-magnitude experimental condition, and experimental condition includes vibration frequency range and adds
Carrying capacity grade；Clipping condition entry submodule is responded, the response clipping condition of each response clipping point is inputted, experimental condition includes limit
Swing frequency range and clipping test magnitude；Actively recessed condition formulates submodule to high-magnitude, according to the defeated of (1) to (4) module
Enter information and successively predict response of each response measuring point under high-magnitude experimental condition by linear relationship, if the response level is super
The clipping magnitude in response clipping condition is crossed, then experimental condition carries out recessed processing.Vibration control system is to all response clippings
The recessed condition of point removes envelope, which is the recessed condition of high-magnitude active formulated；Recessed experimental condition shows and deposits
Submodule is stored up, amplitude-frequency is carried out to the recessed condition of high-magnitude active of formulation and is shown, and is stored with the format of UFF, for vibration
Autocontrol system calls automatically.
Wherein 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 there is n survey
Point, then i=1,2 ..., n).The measurement not only includes the measurement of response point on spacecraft product, also includes in vibration experiment
The measurement of power amplifier output electric current.High-magnitude experimental condition is A (f).It is according to the test data that formula (1) can estimate high-magnitude
Ai(f)。
The prediction experiment data and response clipping condition for comparing each measuring point, if response is more than in response clipping condition
Clipping tests magnitude, then needs to be adjusted high-magnitude experimental condition.
If predicting that the response data of high-magnitude is Ai(f), given response clipping test magnitude isThen with the survey
The corresponding revised high-magnitude condition A of adjustment of point clipping conditioni' (f) can be predicted by formula (2).
It is possible thereby to obtain a series of revised high-magnitude condition AiThe lower envelope of ' (f), comprehensive each response clipping point are bent
Line obtains high-magnitude actively recessed condition.
Actively recessed mechanical condition formulation module not only considers to respond clipping measuring point on spacecraft in vibration control system, together
When the whole capability of vibration experiment is taken into account.The formulation of the recessed condition of high-magnitude active will combine all response clippings
The current signal of measuring point and power amplifier formulates recessed condition to integrate.Actively recessed mechanical condition formulates module in vibration control system
Sinusoidal and random experiment is applicable in.
The present invention has fully considered that actively recessed mechanical condition formulates the required link considered to spacecraft, gets rid of previous system
Fixed condition excessively relies on the experience of testing crew, and needs the drawbacks of largely being calculated；Vibration control system is facilitated simultaneously
The recessed condition of formulation is called automatically, improves test efficiency.
Although the detailed description and description of the specific embodiments of the present invention are given above, it should be noted that
We can carry out various equivalent changes and modification to above embodiment according to the concept of the present invention, and generated function is made
It, should all be within protection scope of the present invention when with the spirit still covered without departing from specification and attached drawing.
Claims (4)
- Mainly include six submodules 1. actively recessed mechanical condition formulates module in vibration control system:(1) low amounts grade experimental condition input submodule inputs the input experimental condition of completed low magnitude vibration test, examination The condition of testing includes vibration frequency range and load magnitude；(2) response clipping point low amounts grade measurement data imports submodule, inputs examination of each measuring point after the completion of the test of low amounts grade Data are tested, data demand is the generalized data file format of UFF；Clipping is responded in addition to considering the crucial survey on spacecraft product Point, while the power amplifier electric current for measuring vibration experiment thrust capacity being taken into account；(3) high-magnitude experimental condition input submodule inputs high-magnitude experimental condition, and experimental condition includes vibration frequency range With load magnitude；(4) clipping condition entry submodule is responded, the response clipping condition of each response clipping point is inputted, experimental condition includes limit Swing frequency range and clipping test magnitude；(5) actively recessed condition formulates submodule to high-magnitude, according to the input information of (1) to (4) step by linear relationship according to Response of the secondary each response measuring point of prediction under high-magnitude experimental condition, if the response level is more than in response clipping condition Clipping magnitude, then experimental condition carries out recessed processing, and vibration control system removes packet to the recessed condition of all response clipping points Network, the envelope are the recessed condition of high-magnitude active formulated；(6) recessed condition is shown and sub-module stored, and to the high-magnitude of formulation, actively recessed condition carries out amplitude-frequency and shows, and with The format of UFF is stored, and is called automatically for vibration control system；Wherein the high-magnitude detailed process that actively recessed condition is formulated is as follows in step (5):If low magnitude vibration experimental condition is a (f), test measurement data are ai(f), which not only includes on spacecraft product The measurement of response point also includes the measurement of power amplifier output electric current in vibration experiment；High-magnitude experimental condition is A (f), according to The test data that formula (1) can estimate high-magnitude is Ai(f),The prediction experiment data and response clipping condition for comparing each measuring point, if response is more than clipping in response clipping condition Magnitude is tested, then needs to be adjusted high-magnitude experimental condition；If predicting that the response data of high-magnitude is Ai(f), given response clipping test magnitude isThen with the measuring point clipping The corresponding revised high-magnitude condition A ' of adjustment of conditioni(f) it is predicted by formula (2),It is possible thereby to obtain a series of revised high-magnitude condition A 'i(f), the lower enveloping curve of comprehensive each response clipping point obtains To the recessed condition of high-magnitude active.
- 2. actively recessed mechanical condition formulates module in vibration control system as described in claim 1, which is characterized in that vibration Actively recessed mechanical condition formulation module registration string and random experiment are applicable in control system.
- 3. actively recessed mechanical condition formulates module in vibration control system as described in claim 1, which is characterized in that actively The formulation of recessed mechanical condition includes the test of sinusoidal and random two class.
- 4. actively recessed mechanical condition formulates module in vibration control system as described in claim 1, which is characterized in that just For string test, experimental condition is change curve of the acceleration amplitude with frequency；For random experiment, experimental condition is Acceleration power spectral density value with frequency change curve.
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| CN109000868B (en) * | 2018-05-07 | 2020-04-07 | 北京空间飞行器总体设计部 | Method for formulating concave condition of spacecraft sinusoidal vibration test |
| 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 |
| CN111595542B (en) * | 2020-05-18 | 2022-03-22 | 北京卫星环境工程研究所 | Spacecraft dynamics test data analysis system |
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| CN105659904B (en) * | 2010-12-10 | 2014-04-09 | 北京空间飞行器总体设计部 | The recessed method of spacecraft parts random vibration acceleration spectrum based on force limited control |
| 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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| JPS63138232A (en) * | 1986-11-29 | 1988-06-10 | Tokyo Electron Ltd | Vibration testing system |
| US6681152B1 (en) * | 2000-11-30 | 2004-01-20 | Bbnt Solutions Llc | Predictive active compensation systems |
| CN105659904B (en) * | 2010-12-10 | 2014-04-09 | 北京空间飞行器总体设计部 | The recessed method of spacecraft parts random vibration acceleration spectrum based on force limited control |
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