CN102384833B - Device and method for testing combination control of multiple excitation sources - Google Patents
Device and method for testing combination control of multiple excitation sources Download PDFInfo
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- CN102384833B CN102384833B CN201110332965.7A CN201110332965A CN102384833B CN 102384833 B CN102384833 B CN 102384833B CN 201110332965 A CN201110332965 A CN 201110332965A CN 102384833 B CN102384833 B CN 102384833B
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Abstract
A device for testing combination control of multiple excitation sources consists of a vibration table, a vibration exciter, a piezoelectric element, an SD vibration control system, a laser vibration meter, an oscillometer, a function signal generator and a direct current stabilized power supply, wherein three output channels D1, D2 and D3 of the SD vibration control system are respectively connected with a piezoelectric actuator in the piezoelectric element, the vibration exciter and the vibration table by power amplifiers of the three channels; the vibration exciter and the vibration table are arranged at the positions of a framework, where a testing piece with greater rigidity is arranged; the piezoelectric element is adhered at the flexible part of the testing piece; a piezoelectric sensor in the piezoelectric element is adhered on the testing piece, and signals us1, us2 and us3 output by the piezoelectric sensor are respectively collected by collecting channels CH4, CH5 and CH6 of the SD vibration control system; and the vibration environment of the testing piece is controlled by the three excitation sources in a combined way. The method for testing the combination control of the multiple excitation sources has four steps. The device and the method have practical values and application prospects in vibration tests for service life or durability of a new batch of large aerospace products in China.
Description
(1) technical field
The present invention relates to a kind of vibration testing method, especially relate to a kind of multiple activation source and jointly control test unit and method, belong to field of active control in structural vibration.
(2) background technology
Aerospace flight vehicle is when high-speed flight, the vibration environment stood is complicated, except the mechanical vibration that engine produces, also comprise rough air during high-speed flight, the multiple distributed vibration sources such as the aerodynamic noise that boundary-layer pulse pneumatic produces, they not only can excitation structure body vibration and also may more weak to rigidity or that aerodynamic arrangement is poor position inspire local resonance or cavity vibration, these vibrations may cause product to wear and tear, destroy, web member loosens or instrument and equipment hydraulic performance decline, produce a series of reliability and permanance (life-span) problem, it is the key factor causing aircraft to produce disaster.These oscillating loads are that concentrated force and distributed force excitation combine mostly, the shaketalle test of simple simulation concentrated force is traditional vibration environment test method, modern aerospace structural vibration endurancing requirement can not be met, need Development of Novel in traditional concentrated force excitation experimental basis can provide the vibration test technology of distributed excitation, to meet life-span or the permanance vibration test demand of the new a collection of large aerospace space product of China.
The present invention proposes a kind of piezoelectric element, vibration test technology that shaking table, vibrator jointly control, for Chinese large-sized aerospace structure permanance and fail-test provide new technology solution route.
Existing vibration test technology mainly comprises single shaft vibration test technology and multi-axes vibration test technology.
(1) single shaft vibration test cannot the multi-freedom-degree vibration environment of model configuration, cannot exposed structure failure of removal pattern in such a case, likely makes to have passed the structure of vibration environment test examination and occurs losing efficacy in actual vibration environment.
(2) multi-freedom-degree vibration excitation is very complicated to the coupling effect of structural response, it encourage with single vibration compared with study carefully competingly have how many difference, be difficult at present make quantitative estimation
(3) multi-axes vibration test technology can apply the vibration stress of different directions simultaneously to tested products, although the multi-freedom-degree vibration environment that single shaft vibration test technology cannot be simulated can be simulated, but this experimental technique is mainly used in the stronger structure of some large-scale rigidity, its vibration stress applied is still centralized stress, inappropriate to the elastic construction that Aero-Space are common, such as rudder of aircraft, engine inlets, empennage etc. are exactly the component that crackle often occurs, and the mainly distributed dynamic aerodynamic force stood encourages.
(3) summary of the invention
(1) object: the object of this invention is to provide a kind of multiple activation source and jointly control test unit and method, the vibration durability test that it is Chinese large-sized Aero-Space flexible structure provides new vibration stress to apply approach, has solved current experimental technique and fully cannot simulate the distributed vibration environment that stands in Aero-Space high-speed aircraft operational process and the problem that cannot carry out sufficient vibration durability examination to it.
(2) technical scheme:
1, a kind of multiple activation source of the present invention jointly controls test unit, it is made up of shaking table, vibrator, piezoelectric element, SD vibration control system, laser vibration measurer, oscillograph, function signal generator and D.C. regulated power supply, position annexation between them, signal trend is: three output channel D1 of SD vibration control system, D2, D3 connect piezoelectric actuator, vibrator and shaking table in piezoelectric element respectively through triple channel power amplifier, and namely SD vibration control system D1, D2, D3 export control signal u
a, u
jzq, u
zdtafter power amplifier amplifies, flow to piezoelectric actuator, vibrator and shaking table respectively; Vibrator and shaking table are placed on the larger frame position of testpieces rigidity, and piezoelectric element sticks in the flexible position (see Fig. 2) of testpieces, and three kinds of exciting sources jointly control testpieces vibration environment; Piezoelectric sensor in piezoelectric element sticks on testpieces, and it outputs signal u
s1, u
s2, u
s4gathered by SD vibration control system acquisition channel CH4, CH5 and CH6 respectively, namely piezoelectric sensor is connected to the corresponding acquisition channel of SD vibration control system.Its annexation, signal trend as shown in Figure 3.
Described shaking table is digital electric vibration experiment, is optional component, requires that its working range is: maximum thrust: 98KN; Peak acceleration: 1176m/s2; Maximum load: 120KG; Frequency range: 5-3000HZ.
Described vibrator is optional component, is mainly used in modal test and aircraft floor resonance test, and the power of an application point can be provided to encourage.
Described piezoelectric element is piezoelectric ceramics chip architecture, comprises piezoelectric actuator, piezoelectric sensor etc., and it can provide body structure surface distributed strain excitation, and its mechanical model also can be simplified to concentrated force and the moment of flexure excitation at its end points place, edge sometimes;
Described SD vibration control system is the JAGUAR multiple-input and multiple-output vibration control system that SD company of the U.S. produces, and has 4 output channels and 36 road acquisition channels, is one of current vibration test control system the most advanced in the world.
Described laser vibration measurer is that German POLYTEC produces, its working range: vibration velocity scope maximum +/-10 meter per second; Double channels acquisition; 18 Zoom Lens; 4 times of digital zooms; Scanning space resolution can reach 5 microns; FFT:3200 line; Laser power 1mw; Measure distance: 0-30 rice.In the present invention for the Sequencing and analysis of testpieces each rank mode, resonant frequency.
Described oscillograph is optional component, is used for observing and the waveform of input/output signal and characteristic parameter thereof in detection experiment process;
Described function signal generator is digit synthesis function signal generator/counter, is optional component, and its exportable sine wave, square wave, sawtooth involve all kinds electric signal such as sine sweep.
Described D.C. regulated power supply is optional component, requires its working range: 0-32V; 0-6A; It is used for providing constant voltage dc source to the control circuit board used in test.
Wherein, the model of this shaking table is D-1000-8;
Wherein, the model of this vibrator is JZK-20 type;
Wherein, this piezoelectric ceramic piece thickness is no more than 3 millimeters, and area is no more than 3 square centimeters;
Wherein, the model of this laser vibration measurer is PSV-400B type laser vibration measurer;
Wherein, this oscillographic model is ADS1042C;
Wherein, the model of this function signal generator is (SP) F40 type;
Wherein, the model of this D.C. regulated power supply is DH1720A-2 type.
Principle of work of the present invention and flow process as follows:
Shaking table can provide the basic excitation of an acting surface, and vibrator can provide the power of an application point to encourage, and piezoelectric element can provide body structure surface distributed strain excitation, and the excitation feature of three kinds of vibration sources is different, and available excitation energy is different.The Coordinated Control in variety encourages source will study the reasonable distribution problem of different driving source test load, various exciting source load applying sequencing problem.Shaking table and vibrator can be assigned to the rigidity of structure larger frame position during load distribution, the control energy providing structural framework main.Piezoelectric element is mainly assigned to the larger position of structural flexibility, provides distributed high frequency pumping.
Test for making multiple activation source and reach Optimal Control, some information of pilot system and test specimen must be input in control system.Adaptive technique is adopted to be conducive to the nonlinear problem occurred in pilot system.Because test is connected to multiple driving source on same test specimen, so can produce interaction between each driving source and between control sensor, the sports bag that namely sensor measurement obtains contains the contribution amount of each sharp source device.For reaching required motion, vibration control system must have the ability to suppress to interact the unnecessary motion brought because of driver, and this ability is called that cross-couplings corrects, most important for this ability multiple activation source is tested.In addition, for reaching the motion of expection, also requiring to carry out phase place and relevant to control, for sinusoidal experiments, can to correct with phase control, the coupling platform that intersects and the real-time closed-loop of limited passage controls to carry out.Multiple activation source sinusoidal experiments can measure amplitude and the phase place of each response with digital filter, and produces the phase relation needed for each response with driving source; For random test, can carry out with the real-time closed-loop that phase control, relevant control, limited passage and cross-couplings correct.In random test, define the sectional view of amplitude and frequency with a spectral density matrix, produce specific relevant and phase relation between different passage with driving source.
The applying method loading available step Stress Control is coordinated in multiple activation source, control objectives is decomposed into the process progressively increased progressively, the complexity controlled with different exciting source or provide the size of hammer vibration energy, progressively well-balanced adjustment.
2, a kind of multiple activation source of the present invention jointly controls test method, and the method concrete steps are as follows:
Step one: arrange testing equipment, SD vibration control system three output channel D1, D2, D3 are connect piezoelectric actuator, vibrator and shaking table respectively through power amplifier, vibrator and shaking table are placed on the larger frame position of testpieces rigidity, piezoelectric actuator and piezoelectric sensor stick in the flexible position (see Fig. 2) of testpieces, and piezoelectric sensor connects the acquisition channel of SD vibration control system.
Step 2: first utilize laser vibration measurer to record the front quadravalence resonant frequency of testpieces during on-test;
Step 3: piezoelectric actuator ultra-precision driving testpieces encourages to provide a distributed, its control signal u
aexported by SD vibration control system D1 output channel; Vibrator, shaking table encourage testpieces front-end and back-end skeleton structure to provide concentrated force, its control signal u respectively
jzq, u
zdtexported by SD vibration control system D2, D3 output channel respectively, piezoelectric sensor S1, S2, S4 are as control sensor, and it outputs signal u
s1, u
s2, u
s4gathered by SD vibration control system acquisition channel CH4, CH5 and CH6 respectively.
Step 4: SD vibration control system inputted vibration spectrum shape, start test, record is analytical test result also.
(3) advantage and effect: a kind of multiple activation source of the present invention jointly controls test unit and method, because piezoelectric element has, vibration stress controllability is good, realization is convenient, particularly be convenient to be distributed in each position of structure in a large number, the advantage of the distributed load of large aerospace space product can be simulated, completely likely as the driving source of life-span and endurancing, and in conjunction with traditional vibrator and shaking table, for the applying testing vibration stress provides new solution route.
(4) accompanying drawing explanation
Fig. 1 aircaft configuration scale model of the present invention
Fig. 2 aircaft configuration scale model of the present invention right flank piezoelectric element arrangement
The front view of Fig. 2 a aircaft configuration scale model of the present invention right flank piezoelectric element arrangement
The vertical view of Fig. 2 b aircaft configuration scale model of the present invention right flank piezoelectric element arrangement
Fig. 3 piezoelectric element of the present invention, shaking table and vibrator jointly control test block diagram
The FB(flow block) of Fig. 4 test method of the present invention
In figure under symbol description figure:
A11-A20 is piezoelectric actuating sheet; S4-S6 is piezoelectric sensor.
(5) embodiment
See Fig. 1, the present invention for testpieces, illustrates test unit and process with aircaft configuration scale model, and testpieces rapidoprint is duralumin (density: 2.8 × 10
3kg/m
3), the thickness of two wing structures is 2mm, select the scale model of aircaft configuration as subjects, mainly because of it, comparatively cantilever mounted girder construction in one end is complicated, both there is the airfoil structure of similar flexible structure, there is again the skeleton structure that rigidity is larger, in order to explore piezoelectric element and traditional excitational equipment as shaking table, the Combined Trials technology of vibrator, to expand the range of application of piezoelectric element and fully to excavate the potentiality of piezoelectric element as the distributed driving source of vibration test, and then find new technological approaches for life-span of modern large aerospace space structure and vibration durability test.
In process of the test, in order to increase driving force, we paste 10 couples of piezoelectric actuating sheet A1-A10 and 3 piezoelectric sensor S1-S3 at left wing's flexible structure upper and lower surface coordination of aircaft configuration scale model, right flank flexible structure upper and lower surface coordination pastes 10 couples of piezoelectric actuating sheet A11-A20 and 3 piezoelectric sensor S4-S6, equally, piezoelectric sensor is only pasted at the upper surface of two wing structures, and their layouts on aircaft configuration scale model are shown in Fig. 2 a, Fig. 2 b.
The testing equipment shaking table that the present invention needs, vibrator, SD vibration control system, laser vibration measurer, oscillograph, function signal generator, D.C. regulated power supply and piezoelectric ceramic piece.Three output channel D1 of SD vibration control system, D2, D3 connect piezoelectric actuator, vibrator and shaking table in piezoelectric element respectively through triple channel power amplifier, namely SD vibration control system D1, D2, D3 export control signal u
a, u
jzq, u
zdtafter power amplifier amplifies, flow to piezoelectric actuator, vibrator and shaking table respectively; Vibrator and shaking table are placed on the larger frame position of testpieces rigidity, and piezoelectric element sticks in the flexible position (see Fig. 2) of testpieces, and three kinds of exciting sources jointly control testpieces vibration environment; Piezoelectric sensor sticks on testpieces, and it outputs signal u
s1, u
s2, u
s4gathered by SD vibration control system acquisition channel CH4, CH5 and CH6 respectively, namely piezoelectric sensor is connected to the corresponding acquisition channel of SD vibration control system, and its control block diagram is shown in Fig. 3.
Piezoelectric effect is the most basic effect of piezoelectric, and it comprises two kinds of phenomenons: one is that just can produce electric charge or voltage in piezoelectric, this phenomenon is called direct piezo electric effect when mechanical force or pressure (strain) act on piezoelectric element; Two is that then this material just can produce mechanical force and strain if when electric charge or voltage put on piezoelectric, and this phenomenon is called inverse piezoelectric effect.We paste some piezoelectric patches by structure to be controlled, utilize its direct piezo electric effect to make structural strain or strain rate sensor (" piezoelectric sensor "); Meanwhile, paste some piezoelectric patches in addition again and by voltage drive, utilize its inverse piezoelectric effect as actuator (" piezoelectric actuator ").
Large scale structure run-of-the-mill is large, the rigidity of its skeleton structure is large, oscillating load is complicated, for ensureing that the vibration test stress of its structure entirety meets the requirement of test profile, sometimes need, in the position that its rigidity is large, traditional excitation set is installed, control the oscillating load of test specimen with piezoelectric element coordinate synchronization.The Coordinated Control in variety encourages source will study the reasonable distribution problem of different driving source test load, various exciting source load applying sequencing problem.Shaking table and vibrator can be assigned to the rigidity of structure larger frame position during load distribution, the control energy providing structural framework main.Piezoelectric element is mainly assigned to the large position of structural flexibility, provides distributed high frequency pumping.
A kind of multiple activation source of the present invention jointly controls test method, and the method concrete steps are as follows:
Step one: arrange testing equipment, SD vibration control system three output channel D1, D2, D3 are connect piezoelectric actuator, vibrator and shaking table respectively through power amplifier, vibrator and shaking table are placed on the larger frame position of testpieces rigidity, piezoelectric actuator and piezoelectric sensor stick in the flexible position (see Fig. 2) of testpieces, piezoelectric sensor (?) connect the acquisition channel of SD vibration control system.
Step 2: first utilize laser vibration measurer to record the front quadravalence resonant frequency of testpieces during on-test;
Step 3: piezoelectric actuator ultra-precision driving testpieces encourages to provide a distributed, its control signal u
aexported by SD vibration control system D1 output channel; Vibrator, shaking table encourage testpieces front-end and back-end skeleton structure to provide concentrated force, its control signal u respectively
jzq, u
zdtexported by SD vibration control system D2, D3 output channel respectively, piezoelectric sensor S1, S2, S4 are as control sensor, and it outputs signal u
s1, u
s2, u
s4gathered by SD vibration control system acquisition channel CH4, CH5 and CH6 respectively;
Step 4: SD vibration control system inputted vibration spectrum shape, start test, record is analytical test result also.
The FB(flow block) of test method of the present invention is shown in Fig. 4.
Claims (2)
1. a multiple activation source jointly controls test unit, it is made up of shaking table, vibrator, piezoelectric element, SD vibration control system, laser vibration measurer, oscillograph, function signal generator and D.C. regulated power supply, it is characterized in that: three output channel D1 of SD vibration control system, D2, D3 connect piezoelectric actuator, vibrator and shaking table in piezoelectric element respectively through triple channel power amplifier, namely SD vibration control system D1, D2, D3 export control signal u
a, u
jzq, u
zdtafter power amplifier amplifies, flow to piezoelectric actuator, vibrator and shaking table respectively; Vibrator and shaking table are placed on the large frame position of testpieces rigidity, and piezoelectric element sticks in the flexible position of testpieces; In process of the test, in order to increase driving force, 10 couples of piezoelectric actuator A1-A10 and 3 piezoelectric sensor S1-S3 is pasted at left wing's flexible structure upper and lower surface coordination of aircaft configuration scale model, right flank flexible structure upper and lower surface coordination pastes 10 couples of piezoelectric actuator A11-A20 and 3 piezoelectric sensor S4-S6, equally, piezoelectric sensor is only pasted at the upper surface of two wing structures; Three kinds of exciting sources jointly control testpieces vibration environment; Piezoelectric sensor in piezoelectric element sticks on testpieces, and it outputs signal u
s1, u
s2, u
s4gathered by SD vibration control system acquisition channel CH4, CH5 and CH6 respectively, namely piezoelectric sensor is connected to the corresponding acquisition channel of SD vibration control system;
Described shaking table is digital electric vibration experiment;
Described vibrator is for modal test and aircraft floor resonance test, provides the power of an application point to encourage;
Described piezoelectric element is piezoelectric ceramics chip architecture, comprises piezoelectric actuator, piezoelectric sensor, and it provides body structure surface distributed strain excitation;
Described SD vibration control system is the JAGUAR multiple-input and multiple-output vibration control system that SD company of the U.S. produces;
Described laser vibration measurer is that German POLYTEC produces, and it is for the Sequencing and analysis of testpieces each rank mode, resonant frequency;
Described oscillograph is used to waveform and the characteristic parameter thereof of input/output signal in observation and detection experiment process;
Described function signal generator is digit synthesis function signal generator/counter, and its sine wave output, square wave, sawtooth involve sine sweep all kinds electric signal;
Described D.C. regulated power supply, its working range: 0-32V; 0-6A; It is used for providing constant voltage dc source to the control circuit board used in test;
Wherein, the step choosing sensor is as follows:
Step one: arrange testing equipment, SD vibration control system three output channel D1, D2, D3 are connect piezoelectric actuator, vibrator and shaking table respectively through power amplifier, vibrator and shaking table are placed on the large frame position of testpieces rigidity, piezoelectric actuator and piezoelectric sensor stick in the flexible position of testpieces, and piezoelectric sensor connects the acquisition channel of SD vibration control system;
Step 2: first utilize laser vibration measurer to record the front quadravalence resonant frequency of testpieces during on-test;
Step 3: piezoelectric actuator ultra-precision driving testpieces encourages to provide a distributed, its control signal u
aexported by SD vibration control system D1 output channel; Vibrator, shaking table encourage testpieces front-end and back-end skeleton structure to provide concentrated force, its control signal u respectively
jzq, u
zdtexported by SD vibration control system D2, D3 output channel respectively, piezoelectric sensor S1, S2, S4 are as control sensor, and it outputs signal u
s1, u
s2, u
s4gathered by SD vibration control system acquisition channel CH4, CH5 and CH6 respectively;
Step 4: SD vibration control system inputted vibration spectrum shape, start test, record is analytical test result also.
2. a kind of multiple activation source according to claim 1 jointly controls test unit, it is characterized in that: wherein, and the thickness of this piezoelectric ceramic piece is no more than 3 millimeters, and area is no more than 3 square centimeters.
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