CN103471705A - Ultra-low frequency six-component micro-vibration measurement system - Google Patents
Ultra-low frequency six-component micro-vibration measurement system Download PDFInfo
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- CN103471705A CN103471705A CN2013104461214A CN201310446121A CN103471705A CN 103471705 A CN103471705 A CN 103471705A CN 2013104461214 A CN2013104461214 A CN 2013104461214A CN 201310446121 A CN201310446121 A CN 201310446121A CN 103471705 A CN103471705 A CN 103471705A
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- 238000005259 measurement Methods 0.000 title abstract description 6
- 238000012545 processing Methods 0.000 claims abstract description 18
- 239000011888 foil Substances 0.000 claims description 12
- 239000000203 mixture Substances 0.000 claims description 8
- 239000004065 semiconductor Substances 0.000 claims description 3
- 238000012360 testing method Methods 0.000 description 11
- 239000011159 matrix material Substances 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
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- 238000013461 design Methods 0.000 description 2
- VIKNJXKGJWUCNN-XGXHKTLJSA-N norethisterone Chemical compound O=C1CC[C@@H]2[C@H]3CC[C@](C)([C@](CC4)(O)C#C)[C@@H]4[C@@H]3CCC2=C1 VIKNJXKGJWUCNN-XGXHKTLJSA-N 0.000 description 2
- 230000003534 oscillatory effect Effects 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
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- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 210000004602 germ cell Anatomy 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
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Abstract
An ultra-low frequency six-component micro-vibration measurement system comprises a base, a loading disk, four folded beams, strain transducers, dynamic strain gages and a data acquiring and processing system, wherein the four folded beams are evenly distributed in the circumferential direction of the lower surface of the loading disk; each folded beam is perpendicular to every two adjacent folded beams, and one end of each folded beam is fixedly connected between the loading disk and the base; the strain transducers are pasted to the folded beams, achieve bridge circuit connection through the strain gages and are connected with the data acquiring and processing system; when a micro vibration source vibrates, the strain transducers measure strain generated by the four folded beams and output a voltage signal to the data acquiring and processing system through the strain gages, and vibration characteristics of the micro vibrating source are analyzed by the data acquiring and processing system according to the input voltage signal. The measurement system can accurately measure the disturbance force of the micro vibrating source and high in measurement accuracy.
Description
Technical field
A kind of high precision ultralow frequency six component microvibration measuring systems of the present invention, can be used for the spacecraft inside vibration signal of tiny perturbation load on six-freedom degree carried out to kinetic measurement.
Background technology
Current spacecraft all belongs to large-scale flexible expansion mechanism mostly, and, with a large amount of optical elements, they have all proposed very high requirement to pointing accuracy and degree of stability.In addition, in modern spacecraft attitude control system, reaction wheel, single frame moment gyro and sun wing driving mechanism etc. are the critical elements in its control system, they are when providing necessary control power, also can cause some nuisance vibrations (for the sake of simplicity, below above-mentioned three germlines completely being called to disturbing source).These disturbances are mainly caused by flywheel imbalance, bearing disturbance, motor disturbance, motor driving error etc., wherein the flywheel imbalance is the main reason that causes the flywheel vibration, these disturbing forces and disturbing moment can reduce the performance index of accuracy instrument in the body space, therefore measure and analyze the dynamic perfromance of spacecraft useful load disturbance, thereby with the safe design of strengthening spacecraft, very important engineering significance is arranged for the attitude control accuracy of analyzing and eliminate disturbance raising spacecraft.
Because the disturbance of spacecraft disturbing source is very little, indivedual useful load are as momenttum wheel three faint disturbances that direction can only produce even a few milli newton of tens milli newton in space, want to measure this type of disturbance very difficult in the ground experiment chamber with relatively strong jamming pattern noise, and the accuracy requirement of its respective sensor is very high.
At present, there is not yet the reported in literature of relevant this type of microvibration measuring system both at home and abroad.
Summary of the invention
The technical problem to be solved in the present invention is: overcome the deficiencies in the prior art, a kind of ultralow frequency six component high-precision microvibration measuring systems are provided, utilize this system can measure and analyze in the spacecraft operational process, the dynamic perfromance of disturbing source on the six-freedom degree of space, for the attitude control accuracy that improves spacecraft and the safe design of strengthening spacecraft provide reliable test data.
The present invention will solve the technical scheme that its technical matters adopts: a kind of ultralow frequency six component microvibration measuring systems comprise base, loading disk, four folded beams, strain transducer, dynamic strain indicator and data acquisition and processing (DAP) systems; Four folded beams are uniform along loading disk lower surface circumferencial direction; Each folded beam and adjacent two folded beams are vertical relation, and folded beam one end is fixedly connected between loading disk and base; Paste strain transducer on folded beam, strain transducer realizes that by dynamic strain indicator the bridge road connects and is connected with the data acquisition and processing (DAP) system; When the microvibration source produces vibration, strain transducer records the strain that four folded beams produce, and arriving the data acquisition and processing (DAP) system by the dynamic strain indicator output voltage signal, the data acquisition and processing (DAP) system analyzes the vibration characteristics in microvibration source according to the voltage signal of input.
Described strain transducer is resistance strain gage or semiconductor gauge.
The folding crossbeam that described folded beam arranges mounting flange by two ends forms, be connected with base with the loading disk of folded beam top, below by mounting flange after folding, on the fold plane of folding rear two crossbeams up and down that form, be processed with two arc-shaped grooves to crossbeam inside.
Described four folded beams form survey sensor, by paste eight half-bridges of foil gauge composition on each folded beam arc-shaped groove bottom rear, realize; Perhaps by the arc surface place on arc-shaped groove bottom rear and each crossbeam, paste a foil gauge, eight foil gauges are arranged on each folded beam, eight full-bridges of whole composition are realized microvibration measuring.
The present invention compared with prior art has the following advantages:
(1) measurement mechanism of the present invention separates with measured test specimen, need to optional equipment and sensor be installed on test specimen, does not affect the dynamic perfromance of test specimen, does not damage the test specimen structure, and after test, test specimen can also normally be used.
(2) the present invention by the reasonable Arrangement of 16 strain transducers, forms eight half-bridges, thereby can record to obtain the moving signal of ultralow frequency perturbation of six-freedom degree, makes measuring accuracy greatly improve.
(3) the present invention can realize by paste eight half-bridges of four foil gauges compositions on each folded beam; Also can paste a foil gauge in the arc surface place on each crossbeam, eight foil gauges are arranged on each folded beam, eight full-bridges of whole composition, further improve transducer sensitivity.
(4) microvibration measuring system volume of the present invention is small and exquisite, can be applied to easily multiple occasion, has improved the applicability of measuring system.
(5) process four arc grooves in the present invention on each folded beam, when the unit under test on being installed on this microvibration measuring system produces disturbance, because stress is concentrated, can make the arc groove bottom produce maximum strain, thereby improve to greatest extent measuring accuracy.
The accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is schematic top plan view of the present invention;
Fig. 3 is with the folded beam structural representation of piezoelectric sensor in the present invention;
Fig. 4 is understructure schematic diagram in the present invention.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in detail, specific as follows:
As shown in Figure 1, 2, at loading disk 2 upper surface definition coordinate system XYZ.A kind of ultralow frequency six component high-precision microvibration measuring systems of the present invention comprise: 16 coupling bolts 1,2,16 strain transducers of loading disk 3, four folded beams 4, base 5, eight bolt holes 6, dynamic strain indicator 7 and data acquisition and processing (DAP) systems 8.Vibration source is arranged on the center of loading disk 2, four folded beams 4 are between base 5 upper surfaces and loading disk 2 lower surfaces, compress and connect by 16 bolts 1,16 strain transducers 3 stick on respectively the upper and lower surface of four folded beams 4, the force and moment in order to sensing lead or vibration source in X, Y and Z-direction; On the XY plane, each folded beam 4 is vertical relation with adjacent two folded beams, and as shown in Figure 2, four folded beams 4 are uniform along loading disk 2 lower surface circumferencial directions, and the installation direction of four folded beams 4 and Z axis are the spatial vertical relation.16 strain transducers 3 form eight half-bridges and are connected with dynamic strain indicator 7 and data acquisition and processing (DAP) system 8 by signal transmssion line; When the microvibration source produces vibration, the strain of 16 strain transducer 3 generations changes into voltage signal by dynamic strain indicator 7, this voltage signal is converted into three microvibration force signals and three microvibration torque signals by data acquisition and processing (DAP) system 8, based on this can accurate analysis goes out the vibration characteristics in microvibration source.
Described 16 strain transducers are resistance strain gage or semiconductor strain piece element.
In this system, base 5 is square aluminium mount structure, and eight counter sinks and four through holes are arranged on framework; Base upper surface mills out four locating slots, mills out four circular arc cutaway on the framework internal border.Its shape as shown in Figure 4.
Loading disk 2 be shaped as circle, be also alumina based material, vibration source is arranged on the center of loading disk 2.The lower surface of loading disk 2 mills out four locating slots and is convenient to install folded beam 4, is distributed with eight counter sinks and four through holes on dish, and counter sink is for connecting folded beam 4, and through hole is for dead load.
As shown in Figure 3; Process two arc-shaped grooves on two crossbeams of each folded beam 4, four folded beams are along loading disk 2 lower surface circumference uniform distributions, and align with base 5 sides in its side.Four folded beams 4 form survey sensor, can realize by paste eight half-bridges of four foil gauges compositions on each folded beam; Also can paste a foil gauge in the arc surface place on each crossbeam, eight foil gauges are arranged on each folded beam, eight full-bridges of whole composition, realize microvibration measuring with this.
The top of base 1 is connected with folded beam 4; Lower part is connected with ground by bolt.Total will guarantee that its rigidity meets the dynamic test requirement.Described base 5 is the square-shaped frame shelf structure, and eight counter sinks and four through holes are arranged on framework, and counter sink is for connecting folded beam 4, and through hole is for being fixed to end machine by base 5; Base 5 upper surfaces mill out four locating slots, for folded beam 4 is installed to location, mill out four circular arc cutaway on the framework internal border so that install.Its shape as shown in Figure 4.
The microvibration measuring system is arranged on ground, microvibration source test specimen is arranged on to the center of loading disk 2, whether the signal that checks 16 strain transducers 3 normally and by dynamic strain indicator 7 completes the connection of bridge road, move afterwards the microvibration source, make it produce vibration, the strain that strain transducer 3 produces is converted into voltage signal through dynamic strain indicator, this voltage signal is converted into three microvibration force signals and three microvibration torque signals by data acquisition and processing (DAP) system 8, based on this can accurate analysis goes out the vibration characteristics in microvibration source.Due to what obtain by data acquisition processing system, it is voltage signal, voltage signal to be converted to force signal, before test, need pair of strain sensors to be demarcated, obtain corresponding sensitivity coefficient, can obtain the force signal of useful load after itself and voltage signal are multiplied each other.The concrete mistake of demarcating is called: will disturb after vibration source is arranged on loading disk, and at its geometric center place, apply one group of known power F, F=[f
xf
yf
zm
xm
ym
z]
h, the matrix that F is a 6 * n, disturb the power of shaking and three and disturb the moment of shaking n point all arranged for three; Now dynamic strain indicator 7 collects 12 voltage signals, and is transferred to data acquisition and processing (DAP) system 8 by signal wire, and 12 voltage signals are designated as to Δ U=[Δ u
1Δ u
2Δ u
3Δ u
4Δ u
5Δ u
6Δ u
7Δ u
8Δ u
9Δ u
10Δ u
12Δ u
12]
h, the matrix that Δ U is 12 * n rank.Make F=W Δ U, wherein W is transition matrix, and W is 6 * 12 rank matrixes, due to F and Δ U known, can try to achieve transition matrix W=F Δ U
h(Δ U Δ U
h)
-1; When the vibrative moment of disturbing source, it is Δ U that dynamic strain indicator 7 gathers 12 voltage signals, now three of disturbing source vibration forces and oscillatory torque can be obtained, its expression formula is: F=W Δ U, wherein W is the transition matrix of having tried to achieve, the vibration force of first three behavior disturbing source of F, the oscillatory torque of rear three behavior disturbing sources.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (4)
1. ultralow frequency six component microvibration measuring systems, is characterized in that: comprise base (5), loading disk (2), four folded beams (4), strain transducer (3), dynamic strain indicator (7) and data acquisition and processing (DAP) system (8); Four folded beams (4) are uniform along loading disk (2) lower surface circumferencial direction; Each folded beam (4) is vertical relation with adjacent two folded beams, and folded beam (4) one ends are fixedly connected between loading disk (2) and base (5); Paste strain transducer (3) on folded beam (4), strain transducer (3) realizes that by dynamic strain indicator (7) the bridge road connects and is connected with data acquisition and processing (DAP) system (8); When the microvibration source produces vibration, strain transducer (3) records the strain that four folded beams (4) produce, and arriving data acquisition and processing (DAP) system (8) by dynamic strain indicator (7) output voltage signal, data acquisition and processing (DAP) system (8) analyzes the vibration characteristics in microvibration source according to the voltage signal of input.
2. ultralow frequency six component microvibration measuring systems according to claim 1, it is characterized in that: described strain transducer (3) is resistance strain gage or semiconductor gauge.
3. ultralow frequency six component microvibration measuring systems according to claim 1, it is characterized in that: the folding crossbeam that described folded beam (4) arranges mounting flange by two ends forms, be connected with base (5) with the loading disk (2) of folded beam top, below by mounting flange after folding, on the fold plane of folding rear two crossbeams up and down that form, be processed with two arc-shaped grooves to crossbeam inside.
4. ultralow frequency six component microvibration measuring systems according to claim 3, it is characterized in that: described four folded beams (4) form survey sensor, by paste eight half-bridges of foil gauge composition on each folded beam arc-shaped groove bottom rear, realize; Perhaps by the arc surface place on arc-shaped groove bottom rear and each crossbeam, paste a foil gauge, eight foil gauges are arranged on each folded beam, eight full-bridges of whole composition are realized microvibration measuring.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104453288A (en) * | 2014-11-20 | 2015-03-25 | 北京卫星环境工程研究所 | Spacecraft damping vibration isolation micro-vibration test chamber |
| CN106768288A (en) * | 2016-12-05 | 2017-05-31 | 北京航空航天大学 | A kind of high precision high rigidity heavy load piezoelectric type decouples microvibration measuring system |
| CN106940243A (en) * | 2017-05-05 | 2017-07-11 | 山东大学 | A kind of six component measurement balances and model for wind tunnel experiment |
| CN107782536A (en) * | 2017-09-14 | 2018-03-09 | 北京空间飞行器总体设计部 | A kind of multi-level micro-vibration system test method and system |
| CN109323834A (en) * | 2018-11-22 | 2019-02-12 | 大连理工大学 | A kind of 6 DOF dynamic force generating apparatus |
| CN112014008A (en) * | 2020-07-28 | 2020-12-01 | 北京电子工程总体研究所 | Three-dimensional force sensor and force measurement system |
| CN113514185A (en) * | 2021-04-27 | 2021-10-19 | 中国重汽集团济南动力有限公司 | Engine suspension triaxial force sensor and adapter device thereof |
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| CN103323098A (en) * | 2013-05-23 | 2013-09-25 | 北京航空航天大学 | Small-sized micro-vibration measurement and control system |
| CN103323097A (en) * | 2013-06-19 | 2013-09-25 | 北京航空航天大学 | Ultra-low frequency high-accuracy micro-vibration measuring system |
| CN203519152U (en) * | 2013-09-26 | 2014-04-02 | 北京空间飞行器总体设计部 | Ultra-low frequency six-component micro-vibration measurement system |
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2013
- 2013-09-26 CN CN2013104461214A patent/CN103471705A/en active Pending
Patent Citations (4)
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| CN101592518A (en) * | 2009-06-24 | 2009-12-02 | 北京航空航天大学 | A kind of high-precision microvibration measuring system |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104453288A (en) * | 2014-11-20 | 2015-03-25 | 北京卫星环境工程研究所 | Spacecraft damping vibration isolation micro-vibration test chamber |
| CN106768288A (en) * | 2016-12-05 | 2017-05-31 | 北京航空航天大学 | A kind of high precision high rigidity heavy load piezoelectric type decouples microvibration measuring system |
| CN106768288B (en) * | 2016-12-05 | 2019-05-03 | 北京航空航天大学 | A kind of high precision high rigidity heavy load piezoelectric type decoupling microvibration measuring system |
| CN106940243A (en) * | 2017-05-05 | 2017-07-11 | 山东大学 | A kind of six component measurement balances and model for wind tunnel experiment |
| CN106940243B (en) * | 2017-05-05 | 2023-09-22 | 山东大学 | Six-component measuring balance and model for wind tunnel experiment |
| CN107782536A (en) * | 2017-09-14 | 2018-03-09 | 北京空间飞行器总体设计部 | A kind of multi-level micro-vibration system test method and system |
| CN109323834A (en) * | 2018-11-22 | 2019-02-12 | 大连理工大学 | A kind of 6 DOF dynamic force generating apparatus |
| CN109323834B (en) * | 2018-11-22 | 2020-04-28 | 大连理工大学 | Six-dimensional dynamic force generating device |
| CN112014008A (en) * | 2020-07-28 | 2020-12-01 | 北京电子工程总体研究所 | Three-dimensional force sensor and force measurement system |
| CN113514185A (en) * | 2021-04-27 | 2021-10-19 | 中国重汽集团济南动力有限公司 | Engine suspension triaxial force sensor and adapter device thereof |
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Application publication date: 20131225 |