CN103472669B - The method of testing of a kind of camera shutter micro-vibration physical simulation test processes system - Google Patents
The method of testing of a kind of camera shutter micro-vibration physical simulation test processes system Download PDFInfo
- Publication number
- CN103472669B CN103472669B CN201310446505.6A CN201310446505A CN103472669B CN 103472669 B CN103472669 B CN 103472669B CN 201310446505 A CN201310446505 A CN 201310446505A CN 103472669 B CN103472669 B CN 103472669B
- Authority
- CN
- China
- Prior art keywords
- camera shutter
- component
- platform
- sensors
- force
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Force Measurement Appropriate To Specific Purposes (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
A kind of camera shutter micro-vibration physical simulation test processes system and method for testing thereof, by data acquisition system (DAS), six component eight sensors disturb the Force meansurement platform that shakes, card extender, acceleration transducer, camera shutter device and controller thereof and display forms.Camera shutter device is arranged on six component eight sensor test boards by card extender, arranges acceleration transducer according to test request on camera shutter simultaneously.Can disturb to six component eight sensors the Force meansurement platform that shakes during camera shutter work and produce small sample perturbations.Data acquisition system six component eight sensor is disturbed and is shaken Force meansurement platform eight sensor signals and by a series of calculating to obtain disturbing the power of shaking, also gather the signal of acceleration transducer to obtain acceleration simultaneously.
Description
Technical field
The present invention relates to the micro-method for testing vibration of a kind of camera shutter, can be used for carrying out kinetic measurement to the vibration signal of spacecraft camera shutter device tiny perturbation load on six-freedom degree.
Background technology
Camera shutter is the main devices of satellite imagery, for controlling the length of time shutter.Due to mass unbalance, the reasons such as bearing mnanufacture defect and noise of motor, shutter produces periodically celestial body and broadband is small disturbs the power of shaking, these disturb modulation and amplification that power of shaking passes through their internal dynamics, can produce considerable influence to the light path pointing accuracy of remote sensing satellite (GF-4) and degree of stability.Consider that shutter device is arranged near imaging device, this impact just seems particularly important.It is many that shutter disturbs the factor needing consideration when the model that shakes is set up, and as rotating speed, bearing collision harmonic wave and inner structure dynamic perfromance, the impact of mounting structure dynamic perfromance etc., makes the foundation of its model, demarcation and inspection have suitable difficulty.
Because the disturbance of spacecraft disturbing source is very little, in space, three directions can only produce the faint disturbance of even a few milli newton of tens milli newton to indivedual useful load such as momenttum wheel, want to measure this type of disturbance in the ground experiment room with relatively strong jamming pattern noise very difficult, and the accuracy requirement of its respective sensor is very high.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiencies in the prior art, there is provided a kind of camera shutter micro-method for testing vibration, measure and analyze the dynamic perfromance of spacecraft camera shutter device on the six-freedom degree of space, for the safe design of the attitude control accuracy and reinforcement spacecraft that improve spacecraft provides reliable test data.
Technical scheme of the present invention is: a kind of camera shutter micro-vibration physical simulation test processes system, comprises camera shutter, hexagon card extender, six component eight sensors disturb shake Force meansurement platform, Data collection and precessing system; Six component eight sensors are disturbed the Force meansurement platform that shakes and are connected with camera shutter by hexagon card extender; Data collection and precessing system is disturbed with six component eight sensors the Force meansurement platform that shakes and is connected; Described Data collection and precessing system comprises data acquisition module and computing machine; Six component eight sensors are disturbed Force meansurement platform measurement of shaking and are obtained the operating micro-vibration data of camera shutter, and deliver to Data collection and precessing system and carry out analyzing and processing, and what obtain camera shutter disturbs the power of shaking.
Also comprising acceleration transducer, disturbing acceleration when shaking for measuring camera shutter.
Described data acquisition module is LMSSCAND III data acquisition module of LMS company.
A method of testing for camera shutter micro-vibration physical simulation test processes system, step is as follows:
1) demarcation dish is arranged on six component eight sensors to disturb and shake on Force meansurement platform, is tightened with bolt; Demarcation dish is a square aluminium dish, and described demarcation is coiled on four sides and is evenly equipped with 3 beating points separately, upper surface is furnished with 4 beating points, and lower surface is disturbed with six component eight sensors the Force meansurement platform that shakes and is connected;
2) firmly hammer 16 beating points knocked successively on demarcation dish into shape, and gather power hammer time-domain signal, the output voltage signal of the Force meansurement platform that shakes disturbed by six component eight sensors when knocking at each, obtains frequency response function;
3) by step 2) frequency response function that obtains obtains calibration matrix;
4) demarcation dish is pulled down;
5) camera shutter is arranged on six component eight sensors by hexagon card extender to disturb and shake on Force meansurement platform, and with bolt tightening;
6) camera shutter energising is started working;
7) six component eight sensors are disturbed the Force meansurement platform that shakes and are tested camera shutter, and voltage time-domain signal when gathering camera shutter work by Data collection and precessing system;
8) voltage time-domain signal step 7) obtained carries out the frequency-region signal that Fourier transform obtains voltage;
9) voltage frequency-region signal step 8) obtained is multiplied with calibration matrix and obtains the frequency-region signal of camera shutter disturbing force;
10) frequency-region signal of camera shutter disturbing force step 9) obtained carries out the time-domain signal that inversefouriertransform can obtain disturbing force, namely completes the process to micro-vibration signal.
The present invention compared with prior art has the following advantages:
(1) the present invention is by the reasonable Arrangement of eight Common piezoelectricity sensors, thus make the micro-disturbance signal of six-freedom degree that existing one-way piezoelectric force snesor can be utilized to measure, overcome the problem lacking high precision three-dimensional sensor, measuring accuracy is improved greatly.Meanwhile, the present invention adopts high precision acceleration transducer can improve acceleration test precision.
(2) measurement mechanism of the present invention is separated with measured test specimen, does not need on test specimen, install optional equipment and sensor, does not affect the dynamic perfromance of test specimen, does not damage test specimen structure, and after test, test specimen can also normally use.
(3) the present invention is by the pretightning force of reasonable adjusting bolt, the accurate measurement that the amplification can carrying out achieving signal has under the actual motion condition in larger quality disturbance source, improves the reliability of measurement.
(4) disturbing source of the present invention can be placed in measuring system inside or outside, improves the adaptability of measuring system.
Accompanying drawing explanation
Fig. 1 is a kind of camera shutter micro-vibration physical simulation test processes system schematic;
Fig. 2 is calibration point position view of the present invention;
Fig. 3 is the inventive method process flow diagram.
Embodiment
As shown in Figure 1, a kind of camera shutter micro-vibration physical simulation test processes system, comprises camera shutter 3, acceleration transducer 4, hexagon card extender 2, six component eight sensor disturbs the Force meansurement platform 1 that shakes, Data collection and precessing system 5; Six component eight sensors are disturbed the Force meansurement platform 1 that shakes and are connected with camera shutter 3 by hexagon card extender 2; Peripheral control unit and the camera shutter 3 that is connected, control the switch of camera shutter 3; Data collection and precessing system 5 is disturbed with six component eight sensors the Force meansurement platform 1 that shakes and is connected; Six component eight sensors are disturbed the Force meansurement platform 1 that shakes and are measured and obtain the operating micro-vibration data of camera shutter 3, and deliver to Data collection and precessing system 5 and carry out analyzing and processing, and what obtain camera shutter 3 disturbs the power of shaking.
Described Data collection and precessing system 5 is made up of LMSSCAND III data acquisition module of LMS company and computing machine.
Acceleration transducer 4 can arrange test micro-Vibration Condition everywhere as required, each sensor is connected with Data collection and precessing system 5 by wire, this physical simulation disposal system accurately can measure the disturbing force in camera shutter 3 microvibration source, and the reliability measured is high.
Hexagon card extender 2 and six component eight sensors are disturbed to shake in the middle of Force meansurement platform 1 and are all left threaded hole, make hexagon card extender 2 and six component eight sensors disturb to shake between Force meansurement platform 1 and be fixed together by bolt.
As shown in Figure 3, the invention provides camera shutter micro-vibration signal disposal route, described voltage signal measurement disturbs on the Force meansurement platform 1 that shakes at six component eight sensors to carry out, and step is as follows:
1) demarcation dish is arranged on six component eight sensors to disturb and shake on Force meansurement platform 1, is tightened with bolt; Demarcation dish is a square aluminium dish, and as shown in Figure 2, demarcation is coiled on four sides and is evenly equipped with 3 beating points separately, upper surface is furnished with 4 beating points, and lower surface is disturbed with six component eight sensors the Force meansurement platform 1 that shakes and is connected; Six component eight sensors are disturbed the Force meansurement platform 1 that shakes and are made up of eight direction piezoelectric transducer, and wherein four piezoelectric sensors are arranged in the horizontal direction, guarantee to test two disturbing forces in the horizontal direction and the disturbing moment around vertical direction; Other four piezoelectric sensors are vertically arranged, guarantee to test disturbing force vertically and two disturbing moments around horizontal direction.
2) firmly hammer 16 beating points knocked successively on demarcation dish into shape, and gather power hammer time-domain signal, the output voltage signal of the Force meansurement platform 1 that shakes disturbed by six component eight sensors when knocking at each, obtains frequency response function;
3) by step 2) frequency response function that obtains calculates calibration matrix;
4) demarcation dish is pulled down;
5) camera shutter 3 is arranged on six component eight sensors to disturb and shake on Force meansurement platform 1, with bolt tightening;
6) camera shutter 3 energising is started working;
7) six component eight sensors are disturbed the Force meansurement platform 1 pair of camera shutter 3 that shakes and are tested, and gather voltage time-domain signal when camera shutter 3 works by Data collection and precessing system 5;
8) voltage time-domain signal step 7) obtained carries out the frequency-region signal that Fourier transform obtains voltage;
9) voltage frequency-region signal step 8) obtained is multiplied with calibration matrix and obtains the frequency-region signal of camera shutter 3 disturbing force;
10) frequency-region signal of camera shutter 3 disturbing force step 9) obtained carries out the time-domain signal that inversefouriertransform can obtain disturbing force, namely completes the process to micro-vibration signal.
First should try to achieve corresponding calibration matrix W (ω), integral calibrating matrix is actually the frequency response function matrix between the response signal of eight piezoelectric force transducers and the load acting on equivalent center point.In the method, equivalent center is the central point of the loading disk upper surface of eight component sensor devices, heart point directly applies three translation power and three moments are had any problem hereinto, supposing that loading disk is on the basis of rigid body herein, the calibrating table that a rigidity is very high is installed, and selects 16 load(ing) points as shown in the figure.According to space force system level theory, 16 load(ing) points selected are utilized can equivalent to go out to act on three translation power and three moments of loading disk geometric center; In Fig. 2, O point is the central point of loading disk upper surface, and table 1 lists the value of each parameter in figure.
Table 1 calibration point location parameter
| Lx/m | Ly/m | Lz/m |
| 0.042 | 0.042 | 0.04 |
Power F is demarcated by 16 in test
1~ F
16obtain the calibration matrix W (ω) of system, the expression formula of the Matrix C in the transition matrix between the loading matrix of the expression actual loaded in test and equivalent load matrix and formula (5) is:
C
1=[010-Lz0-Lx]
T
C
2=[010-Lz00]
T
C
3=[010-Lz0Lx]
T
C
4=[-1000-Lz-Ly]
T
C
5=[-1000-Lz0]
T
C
6=[-1000-LzLy]
T
C
7=[0-10Lz0-Lx]
T
C
8=[0-10Lz00]
T
C
9=[0-10Lz0Lx]
T
C
10=[1000Lz-Ly]
T
C
11=[1000Lz0]
T
C
12=[1000LzLy]
T
C
13=[00-1Ly-Lx0]
T
C
14=[00-1LyLx0]
T
C
15=[00-1-LyLx0]
T
C
16=[00-1-Ly-Lx0]
T
C in above formula
irepresent the transition matrix between load and center equivalent load loaded for i-th time.
Secondly, according to Modal Analysis Theory, N degree of freedom linear system is had:
X(ω)=H(ω)F(ω)(1)
In above formula, X (ω) for response spectra vector (voltage signal), dimension be N × 1; H (ω) is frequency response function matrix, and dimension is N × N; F (ω) is loading spectrum vector, and dimension is N × 1.
Generally, real system is continuous structure particularly, and its number of degrees of freedom, N is very large, can not record the load that the response in all degree of freedom is subject to solve structure.Under normal circumstances, because charge number P to be determined can not be very large, so wish to determine load to be identified by few response data of trying one's best, namely identify load by the partial response of structure.Suppose that charge number undetermined is P, the measuring point number of response is L, and both are all less than total number of degrees of freedom, N of system, therefore:
X(ω)
L×1=H(ω)
L×PF(ω)
P×1(2)
As long as by the known frequency spectrum determining frequency response function matrix and response vector of above formula, just can solve and carry spectrum, and then obtain the time-domain signal of load with inverse fourier transform, the load identification inverse matrix of frequency response namely in Modal Analysis Theory.If charge number P undetermined in formula (2) is i.e. L=P equal to the measuring point number L of response, then frequency response function matrix H (ω) is square formation, and now loading spectrum vector F (ω) can be tried to achieve by following formula:
F(ω)=H
-1(ω)X(ω)(3)
If the measuring point number L of charge number P undetermined and response is unequal, normally L >=P, then frequency response function matrix H (ω) is no longer just square formation, and must ask generalized inverse to frequency response function, like this, the formula of load identification is:
F(ω)=[H
H(ω)H(ω)]
-1H
H(ω)X(ω)(4)
In formula, the conjugate transpose of subscript H representing matrix.Usual dynamic response X (ω) becomes more readily available, and frequency response function matrix H (ω) really rule be not easy, because the reflection of each element is relation between the point of excitation of various discrete and response point in H (ω) matrix, response point is mutually different for each different point of excitation and point of excitation for the frequency response function between each different response point, that is, H (ω) in above formula and F (ω) is closely connected together, if do not know each component F in load vectors F (ω)
j(ω) active position, also just cannot determine each element in H (ω).Therefore, inverse matrix of frequency response can only be used for the dynamic load identifying known action position, then can not identify in this way for active position the unknown or time dependent situation.
For camera shutter, its disturbing force application point can not accurately be determined.Two problems can be run into: 1) how to define disturbing force application point during inverse matrix of frequency response at this moment before application described in face; 2) because the disturbing force application point for definition often cannot direct imposed load, how transfer matrix demarcation is carried out to this application point.
For above-mentioned two problems, solution of the present invention is:
1) the disturbing source mounting disc that processing one is relatively firm, mounting disc inherently frequency is greater than detection frequency more than 3 times, at this moment can think that mounting disc relative system other parts are rigid body;
2) all disturbing forces are equivalent to six the external force load of application point in mounting disc, i.e. three translation power, two moments of flexure and moments of torsion;
3) setting as being rigidly connected between demarcation power point of excitation in mounting disc and its central point O, directly demarcation power being applied to the different application point of this dish and different directions and demarcating.
According to foregoing description, load transfer first will be demarcated to the mounting disc centre of form, that is:
F
6×n(ω)=C
6×nF′
n×n(ω)(5)
In above formula, the n in matrix subscript represents the number of times loaded in test; F represents the load of equivalence to the centre of form, and dimension is 6 × n; The load of F ' expression actual loaded is a diagonal matrix, the F in matrix
ii' equal i-th i time load load value; C represents the transition matrix between the loading matrix of actual loaded and equivalent load matrix, and dimension is 6 × n.
Pass between equivalent load and force sensor signals is:
W
6×8(ω)T
8×n(ω)=F
6×n(ω)(6)
N wherein in matrix subscript represents the number of times loaded in test; W is the inverse of system frequency response function matrix; T is the response signal of eight force snesor, and dimension is 8 × n; F is the equivalent load obtained in formula (3.2.5).From in formula (6), when response matrix T exists the inverse time, have:
W
6×8(ω)=F
6×n(ω)T
-1 n×8(ω)(7)
Consider that the passage of response signal only has 8, in order to improve measuring accuracy, the number of load(ing) point should be greater than response channel number, i.e. n>8, at this moment response matrix T is no longer a square formation, but the matrix of a row full rank, application Generalized Inverses Theory, has:
W
6×8(ω)=F
6×n(ω)T
H(ω)[T(ω)T
H(ω)]
-1(8)
(5) formula is substituted into (8), has:
W
6×8(ω)=C
6×nF′
n×n(ω)T
T(ω)[T(ω)T
T(ω)]
-1（9)
The generalized inverse of the frequency response function matrix H (ω) in the T (ω) difference expression (4) that the matrix W (ω) of formula (9) being tried to achieve in test and test record and response X (ω), just can the equivalent external applied load of certainty annuity, realize center equivalence and demarcate the force signal that the voltage signal obtained by sensor is converted to actual needs, namely
F
6×1(ω)=W
6×8(ω)T
8×1(ω)(10)
Measuring error is checked, and adopts the power hammer transient state method of inspection.
The method of inspection of measuring error is impulse load inspection, utilizes F1, the actual measurement load of F5, F13 with compare by the load responded and calibration matrix reverse goes out, verify the accuracy of calibration matrix.(using during standby measurement momenttum wheel)
The actual measurement equivalent load component of each hammer point to center calibration point comprises 0 and non-zero item, uses F respectively
i 0, F
i 1represent, corresponding inverse value is used
represent, i=1 ~ 6, respectively corresponding Fx, Fy, Fz, Mx, My, Mz.The error of hammer force 0 component and non-zero component is used respectively
represent, error calculation formula is:
The content be not described in detail in instructions of the present invention belongs to the known technology of those skilled in the art.
Claims (1)
1. a method of testing for camera shutter micro-vibration physical simulation test processes system, the system related to comprises camera shutter (3), hexagon card extender (2), six component eight sensors disturb the Force meansurement platform (1) that shakes, Data collection and precessing system (5); Six component eight sensors are disturbed the Force meansurement platform (1) that shakes and are connected with camera shutter (3) by hexagon card extender (2); Data collection and precessing system (5) and six component eight sensors are disturbed the Force meansurement platform (1) that shakes and are connected; Described Data collection and precessing system (5) comprises data acquisition module and computing machine; Six component eight sensors are disturbed Force meansurement platform (1) measurement of shaking and are obtained the operating micro-vibration data of camera shutter (3), and deliver to Data collection and precessing system (5) and carry out analyzing and processing, what obtain camera shutter (3) disturbs the power of shaking; Also comprising acceleration transducer (4), disturbing acceleration when shaking for measuring camera shutter (3); It is characterized in that step is as follows:
1) demarcation dish is arranged on six component eight sensors to disturb and shake on Force meansurement platform (1), is tightened with bolt; Demarcation dish is a square aluminium dish, and described demarcation is coiled on four sides and is evenly equipped with 3 beating points separately, upper surface is furnished with 4 beating points, and lower surface and six component eight sensors are disturbed the Force meansurement platform (1) that shakes and are connected;
2) firmly hammer 16 beating points knocked successively on demarcation dish into shape, and gather power hammer time-domain signal, the output voltage signal of Force meansurement platform (1) that shakes disturbed by six component eight sensors when knocking at each, obtains frequency response function;
3) by step 2) frequency response function that obtains obtains calibration matrix;
4) demarcation dish is pulled down;
5) camera shutter (3) is arranged on six component eight sensors by hexagon card extender (2) to disturb and shake on Force meansurement platform (1), and with bolt tightening;
6) camera shutter (3) energising is started working;
7) six component eight sensors are disturbed the Force meansurement platform (1) that shakes and are tested camera shutter (3), and voltage time-domain signal when gathering camera shutter (3) work by Data collection and precessing system (5);
8) by step 7) the voltage time-domain signal that obtains carries out the frequency-region signal that Fourier transform obtains voltage;
9) by step 8) the voltage frequency-region signal that obtains is multiplied with calibration matrix and obtains the frequency-region signal of camera shutter (3) disturbing force;
10) by step 9) frequency-region signal of camera shutter (3) disturbing force that obtains carries out the time-domain signal that inversefouriertransform can obtain disturbing force, namely completes the process to micro-vibration signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310446505.6A CN103472669B (en) | 2013-09-26 | 2013-09-26 | The method of testing of a kind of camera shutter micro-vibration physical simulation test processes system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310446505.6A CN103472669B (en) | 2013-09-26 | 2013-09-26 | The method of testing of a kind of camera shutter micro-vibration physical simulation test processes system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103472669A CN103472669A (en) | 2013-12-25 |
| CN103472669B true CN103472669B (en) | 2016-01-13 |
Family
ID=49797572
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310446505.6A Active CN103472669B (en) | 2013-09-26 | 2013-09-26 | The method of testing of a kind of camera shutter micro-vibration physical simulation test processes system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103472669B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117528065B (en) * | 2023-12-28 | 2024-04-26 | 深圳市城市公共安全技术研究院有限公司 | Camera disturbance effect evaluation and elimination method, device, equipment and storage medium |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101592518A (en) * | 2009-06-24 | 2009-12-02 | 北京航空航天大学 | A kind of high-precision microvibration measuring system |
| CN101881651A (en) * | 2010-06-18 | 2010-11-10 | 北京航空航天大学 | Small-size portable high-accuracy disturbance measuring system |
| CN201844913U (en) * | 2010-10-27 | 2011-05-25 | 中国科学院西安光学精密机械研究所 | Vibration testing clamp for aerospace camera |
| CN102353443A (en) * | 2011-06-22 | 2012-02-15 | 北京航空航天大学 | Elastic vibration disturbance testing system with adjustable rigidity |
| CN102393594A (en) * | 2011-12-06 | 2012-03-28 | 中国科学院长春光学精密机械与物理研究所 | Aviation mapping camera object lens center type shutter mechanism |
| CN103499381A (en) * | 2013-09-26 | 2014-01-08 | 北京空间飞行器总体设计部 | Camera shutter micro-vibration physical simulation test processing system |
| CN203519146U (en) * | 2013-09-26 | 2014-04-02 | 北京空间飞行器总体设计部 | Camera shutter micro-vibration physical simulation test processing apparatus |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6804615B2 (en) * | 2002-04-03 | 2004-10-12 | Honeywell International Inc. | Method of estimating system dynamics by subsystem transfer function testing |
-
2013
- 2013-09-26 CN CN201310446505.6A patent/CN103472669B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101592518A (en) * | 2009-06-24 | 2009-12-02 | 北京航空航天大学 | A kind of high-precision microvibration measuring system |
| CN101881651A (en) * | 2010-06-18 | 2010-11-10 | 北京航空航天大学 | Small-size portable high-accuracy disturbance measuring system |
| CN201844913U (en) * | 2010-10-27 | 2011-05-25 | 中国科学院西安光学精密机械研究所 | Vibration testing clamp for aerospace camera |
| CN102353443A (en) * | 2011-06-22 | 2012-02-15 | 北京航空航天大学 | Elastic vibration disturbance testing system with adjustable rigidity |
| CN102393594A (en) * | 2011-12-06 | 2012-03-28 | 中国科学院长春光学精密机械与物理研究所 | Aviation mapping camera object lens center type shutter mechanism |
| CN103499381A (en) * | 2013-09-26 | 2014-01-08 | 北京空间飞行器总体设计部 | Camera shutter micro-vibration physical simulation test processing system |
| CN203519146U (en) * | 2013-09-26 | 2014-04-02 | 北京空间飞行器总体设计部 | Camera shutter micro-vibration physical simulation test processing apparatus |
Non-Patent Citations (1)
| Title |
|---|
| 空间相机的颤振成像调制传递函数及仿真实验;张影;《光学精密工程》;20110930;第19卷(第09期);第2146-2153页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103472669A (en) | 2013-12-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103499387B (en) | Micro-vibration signal processing method | |
| Ramos | Damage identification on masonry structures based on vibration signatures | |
| Au et al. | Field observations on modal properties of two tall buildings under strong wind | |
| JP4992084B2 (en) | Structure damage diagnostic system and method | |
| CN102506986B (en) | Test system and method for mode and vibration of self-supporting tower and large-span power transmission tower | |
| CN112504595B (en) | Micro-vibration influence measuring device and method for space-oriented measuring instrument | |
| Au et al. | Ambient modal identification of a primary–secondary structure by Fast Bayesian FFT method | |
| US20160109323A1 (en) | Method for analyzing measured signal in resonance fatigue test and apparatus using the same | |
| CN109839441B (en) | Bridge modal parameter identification method | |
| CN106017833B (en) | A kind of performance test methods of high-damping micro-vibration isolation device | |
| Law et al. | Structural damage detection from coupling forces between substructures under support excitation | |
| US7730762B2 (en) | Device and method for testing isolation structure | |
| CN106289619A (en) | A kind of high precision high rigidity six-dimensional force measuring table | |
| CN109299539A (en) | A method of utilizing curvilinear corner index evaluation cantilever beam rigidity weak link | |
| CN106918389A (en) | It is a kind of based on the vibration modal analysis method of doppler optical displacement method and its application | |
| CN103472669B (en) | The method of testing of a kind of camera shutter micro-vibration physical simulation test processes system | |
| CN101881651A (en) | Small-size portable high-accuracy disturbance measuring system | |
| CN103528668B (en) | A kind of refrigeration machine micro-vibration physical simulation test processes system and method for testing thereof | |
| Huras et al. | Quantifying local stiffness loss in beams using rotation rate sensors | |
| CN103674224B (en) | The micro-method for testing vibration of a kind of solar wing driving mechanism | |
| Fritzen et al. | Application of model-based damage identification to a seismically loaded structure | |
| CN110457858A (en) | Based on the determination method of the skyscraper modal vibration main shaft of twin shaft actual measureed value of acceleration | |
| STAKHOVA | Monitoring System of Vibroacoustic Parameters of a Working Zone | |
| CN106052989A (en) | Apparatus for testing performances of high-damping and micro-amplitude vibration isolator | |
| Zhao et al. | Sensor module based on the wireless sensor network for the dynamic stress on the flexible object with large deformation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |