CN103323097A - Ultra-low frequency high-accuracy micro-vibration measuring system - Google Patents
Ultra-low frequency high-accuracy micro-vibration measuring system Download PDFInfo
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- CN103323097A CN103323097A CN201310244981XA CN201310244981A CN103323097A CN 103323097 A CN103323097 A CN 103323097A CN 201310244981X A CN201310244981X A CN 201310244981XA CN 201310244981 A CN201310244981 A CN 201310244981A CN 103323097 A CN103323097 A CN 103323097A
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Abstract
The invention discloses an ultra-low frequency high-accuracy micro-vibration measuring system which is composed of a base, four adapter blocks, four strain-type force sensors, a load disc, a dynamic strain indicator, 48 strain gages and a data collecting and processing system. The strain gages are pasted on the strain-type force sensors. The strain-type force sensors are located between the load disc and the adapter blocks and are connected between the load disc and the adapter blocks in a tightened mode through bolts. The adapter blocks are located on the side surface of the base and connected with the side surface of the base in a tightened mode through bolts. Three dynamic forces and three dynamic force moments of a disturbance source are measured through the fact that the strain gages pasted on the strain-type force sensors are reasonably combined and connected with the dynamic strain indicator to form 12 full bridge circuits. The disturbance source can be installed inside the measuring system and can also be installed outside the measuring system. The strain gages are connected with the dynamic strain indicator through wires. The dynamic strain indicator is connected with the data collecting and processing system through a wire. The ultra-low frequency high-accuracy micro-vibration measuring system can accurately measure the vibratory force and the vibratory force moment of a tiny disturbance source, the measured frequency range is accurate to 0Hz, and the measuring reliability is high.
Description
Technical field
The present invention relates to a kind of ultralow frequency high-precision microvibration measuring system, can be used for the spacecraft inside vibration signal of tiny perturbation load on six-freedom degree carried out kinetic measurement.
Background technology
Present 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 in the control power that necessity is provided, also can cause some nuisance vibrations (for the sake of simplicity, the below is referred to as disturbing source with above-mentioned three kinds of systems).These disturbances are mainly caused by flywheel imbalance, bearing disturbance, motor disturbance, motor-driven error etc., wherein the motor disturbance is the main reason that causes the vibration of sun wing driving mechanism, and the low frequency region situation of motor disturbance is complicated, these disturbing forces and disturbing moment can reduce the performance index of accuracy instrument in the body space, so the dynamic perfromance of measurement and the disturbance of analysis spacecraft useful load, thereby for the safe design of the attitude control accuracy of analyzing and eliminate disturbance raising spacecraft and reinforcement spacecraft very important engineering significance is arranged.
Because the disturbance of spacecraft disturbing source is very little, indivedual useful load such as momenttum wheel be three faint disturbances that direction can only produce tens milli newton even a few milli newton in the space, want in the ground experiment chamber with relatively strong jamming pattern noise, to measure this type of disturbance very difficult, and the accuracy requirement of its respective sensor is very high.In addition, piezoelectric force transducer is lower in the low frequency region degree of accuracy, can not satisfy the test request to the vibration of sun wing driving mechanism.
At present, there is not yet the reported in literature of relevant this type of ultralow frequency 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 high-precision microvibration measuring system is provided, measure and analyze in the spacecraft operational process, the dynamic perfromance of disturbing source on the six-freedom degree of space, overcome piezoelectric force transducer in the lower deficiency of low frequency region degree of accuracy, 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 high-precision microvibration measuring system, and its survey frequency can be low to moderate 0Hz, and the precision of its vibration force and oscillatory torque is better than respectively 10
-3N and 10
-3Nm; This measuring system comprises base 1, device for measuring force 2, dynamic strain indicator 3 and data acquisition and processing (DAP) system 4; Device for measuring force 2 is comprised of four strain force sensors 5, four transfer blocks 6, loading disk 7 and 48 foil gauges 11; Four transfer blocks 6 lay respectively on four side surfaces of base 1, each transfer block 6 all by three bolt tightenings on the side surface of base 1; Four strain force sensors 5 are between the upper surface and loading disk 7 lower surfaces of four transfer blocks 6, and each strain force sensor 5 passes through respectively four bolt tightenings in the upper surface of transfer block 6 and the lower surface of loading disk 7; Four strain force sensors 5 all are comprised of three identical parts of shape, wherein two parts are positioned on the horizontal direction, another part is positioned on the vertical direction, and every part is all posted 4 foil gauges 11 at place, planimetric position corresponding to circular arc, four foil gauges 11 of every part and dynamic strain indicator 3 form a full-bridge, consist of like this full-bridge 8 on two horizontal directions, 9 and vertical direction on full-bridge 10, full-bridge 8 on two horizontal directions, 9 guarantee to measure along the vibration force of Z axis with around X, the oscillatory torque of Y-axis, the full-bridge 10 on the vertical direction guarantee to measure along X, the vibration force of Y-axis and around the oscillatory torque of Z axis; Foil gauge 11 on four strain force sensors 5 links to each other with dynamic strain indicator 3 by signal transmssion line; Dynamic strain indicator 3 outputs link to each other with data acquisition and processing (DAP) system 4 by signal transmssion line; When the small sample perturbations source produces vibration, foil gauge 11 on four strain force sensors 5 produces voltage signal with the full-bridge that dynamic strain indicator 3 forms, this voltage signal is converted into three microvibration force signals and three microvibration torque signals by data acquisition and processing (DAP) system 4, and accurate analysis goes out the vibration characteristics in small sample perturbations source based on this.
Principle of the present invention is: the present invention includes base, four transfer blocks, four strain force sensors, 48 foil gauges, loading disk, dynamic strain indicator and data acquisition and processing (DAP) systems; Disturbing source is installed in the center of loading disk, and the full-bridge that the foil gauge of pasting on the horizontal component of four strain force sensors and dynamic strain indicator form is used for measuring the oscillatory torque of the vibration force of Z direction and X, Y-direction; The full-bridge that the foil gauge of pasting on the vertical part of four strain force sensors and dynamic strain indicator form is used for measuring X, the vibration force of Y-direction and the oscillatory torque of Z direction; The foil gauge of pasting on four strain force sensors links to each other with dynamic strain indicator by signal transmssion line; Dynamic strain indicator output links to each other with the data acquisition and processing (DAP) system by signal transmssion line; When the small sample perturbations source produces vibration, the full-bridge that the foil gauge of pasting on four strain force sensors and dynamic strain indicator form produces voltage signal, this voltage signal is converted into three microvibration force signals and three microvibration torque signals by the data acquisition and processing (DAP) system, based on this can accurate analysis goes out the vibration characteristics in small sample perturbations source.
Described four transfer blocks are piece of stainless steel, and are distributed in symmetrically on four side surfaces of base.
Described four strain force sensors are the aluminum element, post foil gauge on it.
Described four strain force sensors lay respectively on the upper surface of four transfer blocks, and are distributed in symmetrically on the loading disk lower surface, and are positioned at the edge of loading disk.
Described loading disk be shaped as inner circle foreign side.
Four sides, the top of described base are connected with four transfer blocks respectively; The bottom is connected with ground by 20 bolts.
The bolt at the described needs place of being bolted must be tightened in the scope that intensity allows as far as possible, to improve the rigidity of this measuring system, guarantees its measuring accuracy.
Described measuring system inside is empty, disturbing source can be installed in measuring system inside, also disturbing source can be installed in the measuring system outside.
The present invention compared with prior art has the following advantages:
(1) the present invention carries out reasonable Arrangement by the full-bridge that the foil gauge pasted on four common strain force sensors and dynamic strain indicator are formed, thereby so that the moving signal of the perturbation of six-freedom degree can utilize existing strain force sensor to measure, overcome the problem that lacks high precision three-dimensional sensor, so that measuring accuracy improves greatly.
What (2) the present invention used is strain force sensor, can overcome the lower deficiency of piezoelectric force transducer low frequency region degree of accuracy.
(3) measurement mechanism of the present invention separates with measured test specimen, need to optional equipment and sensor be installed at measured test specimen, does not affect the dynamic perfromance of test specimen, does not damage the test specimen structure, tests complete rear test specimen and can also normally use.
(4) disturbing source of the present invention can place measuring system inner or outside, has improved the adaptability of measuring system.
Description of drawings
Fig. 1 is the structural representation of the embodiment of the invention 1;
Fig. 2 is device for measuring force schematic diagram in the embodiment of the invention 1;
Fig. 3 is strain force sensor schematic diagram in the embodiment of the invention 1;
Fig. 4 is full-bridge circuit schematic diagram in the embodiment of the invention 1.
Embodiment
Such as Fig. 1, Fig. 2 and shown in Figure 3, a kind of ultralow frequency high-precision microvibration measuring system comprises: base 1, device for measuring force 2, dynamic strain indicator 3 and data acquisition and processing (DAP) system 4; Device for measuring force 2 is comprised of four strain force sensors 5, four transfer blocks 6 and loading disk 7; Four transfer blocks 6 lay respectively on four side surfaces of base 1, each transfer block 6 all by three bolt tightenings on the side surface of base 1; Four strain force sensors 5 are between the upper surface and loading disk 7 lower surfaces of four transfer blocks 6, and each strain force sensor 5 passes through respectively four bolt tightenings in the upper surface of transfer block 6 and the lower surface of loading disk 7; Four strain force sensors 5 all are comprised of three identical parts of shape, wherein two parts are positioned on the horizontal direction, another part is positioned on the vertical direction, and every part is all posted 4 foil gauges 11 at place, planimetric position corresponding to circular arc, four foil gauges 11 and the dynamic strain indicator 3 of every part can form a full-bridge, full-bridge 8 on the horizontal direction, 9 guarantees that it can measure along the vibration force of Z axis with around the oscillatory torque of X, Y-axis, and the full-bridge 10 on the vertical direction guarantees that it can measure along the vibration force of X, Y-axis with around the oscillatory torque of Z axis; Foil gauge 11 on four strain force sensors 5 links to each other with dynamic strain indicator 3 by signal transmssion line; Dynamic strain indicator 3 outputs link to each other with data acquisition and processing (DAP) system 4 by signal transmssion line; When the small sample perturbations source produces vibration, foil gauge 11 on four strain force sensors 5 produces voltage signal with the full-bridge that dynamic strain indicator 3 forms, this voltage signal is converted into three microvibration force signals and three microvibration torque signals by data acquisition and processing (DAP) system 4, and accurate analysis goes out the vibration characteristics in small sample perturbations source based on this.
Aluminium frame base is tightened with ground by 20 bolts and is connected, and total will guarantee that its rigidity satisfies the dynamic test requirement.
Fig. 3 is the strain force sensor schematic diagram, be pasted with altogether 12 foil gauges on this sensor, this sensor base is fixed, when it was subject to power along the Y positive dirction, the strain of foil gauge 11.1-11.8 can be ignored, because the circular arc effect, foil gauge 11.9 places strain is for negative, foil gauge 11.10 places strain is being for just, and foil gauge 11.11 places strain is for negative, and foil gauge 11.12 places strain is for just; Just have in the strain of foil gauge 11.9-11.12 two for just two for negative, will then can record a voltage signal in these four foil gauges access full-bridge circuits; When it is subject to power along the Z negative direction, because circular arc effect, foil gauge 11.2,11.3,11.5, the strain of 11.8 places are for just, foil gauge 11.1,11.4,11.6,11.7 strains are for negative, this moment, foil gauge 11.1,11.2,11.7,11.8 can form a full-bridge, foil gauge 11.3,11.4,11.5,11.6 can form a full-bridge, and in these two full-bridges two negative strains of two normal strains is arranged all, and this moment, foil gauge 11.9-11.12 places strain can be ignored.Therefore, 48 foil gauges pasting on four strain force sensors can form 12 full-bridges, by four strain force sensors are arranged the measurement that can realize three vibration forces of disturbing source and three oscillatory torques according to position explained above.）
Fig. 4 is the full-bridge circuit schematic diagram, and the resistance of four foil gauges 11 of access full-bridge circuit is R, and the input voltage of access full-bridge circuit is U, and the output voltage of full-bridge circuit is Δ U; Wherein U is provided by dynamic strain indicator 3, and Δ U is because the foil gauge distortion produces, and access dynamic strain indicator 3; Have 48 foil gauges 11 among the present invention, can form 12 full-bridge circuits; When disturbing source produced vibration, owing to 4 strain force sensors 5 foil gauge 11 that causes pasting thereon that deforms deforms, thereby 12 full-bridge circuits all produced output voltage Δ U; Dynamic strain indicator 3 collects 12 Δ U and is transferred to the data acquisition and processing (DAP) system by signal wire.
Ultralow frequency high precision microvibration measuring system is installed on the ground, with small sample perturbations source test specimen be installed in loading disk 7 in the heart, whether the signal that checks the foil gauge 11 of pasting on four strain force sensors 5 is normal, move afterwards the small sample perturbations source, make it produce vibration, thereby make the foil gauge 11 of stickup on four strain force sensors 5 and the full-bridge generation voltage signal that dynamic strain indicator 3 forms, this voltage signal is converted into three microvibration force signals and three microvibration torque signals by data acquisition and processing (DAP) system 6, based on this can accurate analysis goes out the vibration characteristics in small sample perturbations source.Because what obtain by data acquisition and processing (DAP) system 4 is the foil gauge pasted on the strain force sensor 5 and the voltage signal of the full-bridge of dynamic strain indicator 3 compositions, voltage signal to be converted to force signal, also need device for measuring force 2 is demarcated, obtain corresponding transition matrix, can obtain the force signal of useful load after itself and voltage signal are multiplied each other.Calibration process can be finished at special calibrating device.
In a word, measuring system of the present invention can accurately be measured the vibration force in small sample perturbations source, and the frequency range of measurement can be as accurate as 0Hz, and the reliability of measuring is high.
The non-elaborated part of the present invention belongs to techniques well known.
The above; only be part embodiment of the present invention, but protection scope of the present invention is not limited to this, any those skilled in the art are in the technical scope that the present invention discloses; the variation that can expect easily or replacement all should be encompassed within protection scope of the present invention.
Claims (8)
1. a ultralow frequency high-precision microvibration measuring system is characterized in that comprising: base (1), device for measuring force (2), dynamic strain indicator (3) and data acquisition and processing (DAP) system (4); Device for measuring force (2) is comprised of four strain force sensors (5), four transfer blocks (6), loading disk (7) and 48 foil gauges (11); Four transfer blocks (6) lay respectively on four side surfaces of base (1), each transfer block (6) all by three bolt tightenings on the side surface of base (1); Four strain force sensors (5) are positioned between the upper surface and loading disk (7) lower surface of four transfer blocks (6), and each strain force sensor (5) passes through respectively four bolt tightenings in the upper surface of transfer block (6) and the lower surface of loading disk (7); Four strain force sensors (5) all are comprised of three identical parts of shape, wherein two parts are positioned on the horizontal direction, another part is positioned on the vertical direction, and every part is all posted 4 foil gauges (11) at place, planimetric position corresponding to circular arc, four foil gauges (11) of every part and dynamic strain indicator (3) form a full-bridge, consist of like this full-bridge (8 on two horizontal directions, 9) and the full-bridge on the vertical direction (10), full-bridge (8 on two horizontal directions, 9) guarantee to measure along the vibration force of Z axis with around X, the oscillatory torque of Y-axis, the full-bridge on the vertical direction (10) guarantee to measure along X, the vibration force of Y-axis and around the oscillatory torque of Z axis; Foil gauge (11) on four strain force sensors (5) links to each other with dynamic strain indicator (3) by signal transmssion line; Dynamic strain indicator (3) output links to each other with data acquisition and processing (DAP) system (4) by signal transmssion line; When the small sample perturbations source produces vibration, foil gauge (11) on four strain force sensors (5) produces voltage signal with the full-bridge that dynamic strain indicator (3) forms, this voltage signal is converted into three microvibration force signals and three microvibration torque signals by data acquisition and processing (DAP) system (4), and accurate analysis goes out the vibration characteristics in small sample perturbations source based on this.
2. ultralow frequency high-precision microvibration measuring system according to claim 1 is characterized in that: described four transfer blocks (6) are piece of stainless steel, and are distributed in symmetrically on four side surfaces of base (1).
3. ultralow frequency high-precision microvibration measuring system according to claim 1, it is characterized in that: described four strain force sensors (5) are the aluminum element, each strain force sensor (5) all is comprised of three identical parts of shape, wherein two parts are positioned on the horizontal direction, another part is positioned on the vertical direction, and every part is all posted 4 foil gauges (11) at place, planimetric position corresponding to circular arc.
4. ultralow frequency high-precision microvibration measuring system according to claim 1, it is characterized in that: described four strain force sensors (5) lay respectively on the upper surface of four transfer blocks (6), and be distributed in symmetrically on loading disk (7) lower surface, and be positioned at the edge of loading disk (7).
5. ultralow frequency high-precision microvibration measuring system according to claim 1 is characterized in that: described loading disk (7) be shaped as inner circle foreign side.
6. ultralow frequency high-precision microvibration measuring system according to claim 1, it is characterized in that: four sides, the top of described base (1) are connected with four transfer blocks (6) respectively; The bottom is connected with ground by 20 bolts.
7. ultralow frequency high-precision microvibration measuring system according to claim 1, it is characterized in that: the bolt of coupling part, the described needs place of being bolted must be tightened in the scope that intensity allows as far as possible, to improve the rigidity of this measuring system, guarantee its measuring accuracy.
8. ultralow frequency high-precision microvibration measuring system according to claim 1, it is characterized in that: described measuring system inside is empty, disturbing source can be installed in measuring system inside, also disturbing source can be installed in the measuring system outside.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103471705A (en) * | 2013-09-26 | 2013-12-25 | 北京空间飞行器总体设计部 | Ultra-low frequency six-component micro-vibration measurement system |
| CN103471706A (en) * | 2013-09-26 | 2013-12-25 | 北京空间飞行器总体设计部 | Micro-vibration test system of solar array drive 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 |
| CN104122331A (en) * | 2014-07-24 | 2014-10-29 | 北京大学 | Non-destructive testing system and method based on contact vibration of piezoelectric disk |
| CN104567934A (en) * | 2015-01-22 | 2015-04-29 | 中航捷锐（北京）光电技术有限公司 | Jig for vibration test of fiber-optic gyroscope and testing method |
| CN105606202A (en) * | 2015-12-22 | 2016-05-25 | 中国科学院长春光学精密机械与物理研究所 | High-precision ultralow frequency six-dimensional force micro-vibration measuring system |
| CN105973455A (en) * | 2016-06-27 | 2016-09-28 | 北京空间飞行器总体设计部 | Combined piezoelectric strain vibration measurement device |
| CN109990888A (en) * | 2019-03-25 | 2019-07-09 | 中国科学院长春光学精密机械与物理研究所 | A kind of wide range power measuring mechanism |
| 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 |
| CN112444365A (en) * | 2020-11-30 | 2021-03-05 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency modal testing method based on force hammer swing method and laser Doppler method |
| 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 |
| CN114061872A (en) * | 2021-09-14 | 2022-02-18 | 北京航空航天大学 | Three-dimensional high-precision calibration system and method |
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| CN101881651A (en) * | 2010-06-18 | 2010-11-10 | 北京航空航天大学 | Small-size portable high-accuracy disturbance measuring system |
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| JPH0921720A (en) * | 1995-07-03 | 1997-01-21 | Kuratsuki:Kk | Method for analyzing vibration of structure |
| 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 (16)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103471706B (en) * | 2013-09-26 | 2016-06-01 | 北京空间飞行器总体设计部 | A kind of micro-vibration test system of solar wing driving mechanism |
| CN103471706A (en) * | 2013-09-26 | 2013-12-25 | 北京空间飞行器总体设计部 | Micro-vibration test system of solar array drive 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 |
| CN103471705A (en) * | 2013-09-26 | 2013-12-25 | 北京空间飞行器总体设计部 | Ultra-low frequency six-component micro-vibration measurement system |
| CN104122331A (en) * | 2014-07-24 | 2014-10-29 | 北京大学 | Non-destructive testing system and method based on contact vibration of piezoelectric disk |
| CN104567934B (en) * | 2015-01-22 | 2017-05-24 | 中航捷锐（北京）光电技术有限公司 | Jig for vibration test of fiber-optic gyroscope and testing method |
| CN104567934A (en) * | 2015-01-22 | 2015-04-29 | 中航捷锐（北京）光电技术有限公司 | Jig for vibration test of fiber-optic gyroscope and testing method |
| CN105606202A (en) * | 2015-12-22 | 2016-05-25 | 中国科学院长春光学精密机械与物理研究所 | High-precision ultralow frequency six-dimensional force micro-vibration measuring system |
| CN105973455A (en) * | 2016-06-27 | 2016-09-28 | 北京空间飞行器总体设计部 | Combined piezoelectric strain vibration measurement device |
| CN109990888A (en) * | 2019-03-25 | 2019-07-09 | 中国科学院长春光学精密机械与物理研究所 | A kind of wide range power measuring mechanism |
| 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 |
| CN112444365A (en) * | 2020-11-30 | 2021-03-05 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency modal testing method based on force hammer swing method and laser Doppler method |
| CN112444365B (en) * | 2020-11-30 | 2023-08-29 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency mode testing method |
| 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 |
| CN114061872A (en) * | 2021-09-14 | 2022-02-18 | 北京航空航天大学 | Three-dimensional high-precision calibration system and method |
| CN114061872B (en) * | 2021-09-14 | 2023-06-16 | 北京航空航天大学 | Three-dimensional high-precision calibration system and method |
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