CN105509870A - High-precision magneto-electric vibration measurement device for aviation - Google Patents
High-precision magneto-electric vibration measurement device for aviation Download PDFInfo
- Publication number
- CN105509870A CN105509870A CN201510960675.5A CN201510960675A CN105509870A CN 105509870 A CN105509870 A CN 105509870A CN 201510960675 A CN201510960675 A CN 201510960675A CN 105509870 A CN105509870 A CN 105509870A
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- CN
- China
- Prior art keywords
- measurement device
- steel component
- vibration measurement
- column jecket
- magnetic steel
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- 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.)
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H11/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties
- G01H11/02—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by magnetic means, e.g. reluctance
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention discloses a high-precision magneto-electric vibration measurement device for aviation. The device is composed of a column jacket, a magnet steel component, a coil component and springs, wherein the magnet steel component penetrates through the column jacket, the shafts at the two ends of the magnet steel component are each sleeved with one spring, and the coil component is positioned and assembled outside the column jacket. In particular, the two ends of the column jacket are each connected with a bearing seat component which is formed by assembling a rigid seat cover and a ball bearing together, wherein the rigid seat covers are connected and fixed to the column jacket, and the middle of the inner side of each rigid seat cover is provided with circular-bottom grooves in the radial direction, the ball bearings are each provided with a shaft sleeve and three balls in radial distribution, the balls abut against the circular-bottom grooves, and the shafts of the magnet steel component are positioned in the shaft sleeves in a penetrating manner. The vibration measurement device of the invention is compact in structure, light and stable in connection. Material wear is minimized, dimension deviation caused by wear is avoided, and the use requirements of aviation products are fully satisfied.
Description
Technical field
The present invention relates to one and utilize magneto-electric principle, by oscillatory system to-and-fro movement, export the high reliability vibration measurement device of high precision vibration signal.
Background technology
For measuring aeromotor variant position vibration data (vibration velocity, vibration displacement, vibration acceleration), need a kind of high performance vibration measurement device, and this traditional apparatus structure as shown in Figure 1, form primarily of shell 1, coil 3, magnetic steel component 2 and spring 4 attaching.The wearing and tearing that disadvantage maximum in this structure produces after being to ensure for a long time rubbing action repeatedly, spring and magnet steel combine all the time along motion of main shaft, so cannot meet the needs of the high-accuracy test of aeronautical product.
Summary of the invention
In view of the defect that above-mentioned prior art exists, the object of the invention is to propose a kind of high precision magneto-electric aviation vibration measurement device, the high precision solving vibration measurement device maintains problem.
Object of the present invention, to be achieved by the following technical programs: a kind of high precision magneto-electric aviation vibration measurement device, by column jecket, magnetic steel component, coil block and spring are formed, described magnetic steel component is connected in column jecket and the axle at magnetic steel component two ends is all arranged with spring, described coil block location is secured to outside column jecket, it is characterized in that: the both ends of described column jecket are all equipped with the bearing block assembly be made up of rigidity cover for seat and ball bearing attaching, wherein said rigidity cover for seat connects fixing with column jecket and rigidity cover for seat middle inside radial direction is provided with round bottom groove, described ball bearing is provided with axle sleeve and radially-arranged three balls, and ball abuts in round bottom groove, the axle cross-under of magnetic steel component is positioned in axle sleeve.
Further, described ball bearing to be provided with the roller of end face rolling friction between two between ball.
Further, described rigidity cover for seat is split socket joint type structure, comprises the abutting block of shell and interior band round bottom groove thereof, abuts between block and shell and is provided with elasticity fitting.
Remarkable result after technical solution of the present invention application implementation is: this vibration measurement device compact conformation, light and handy, stable connection, the abrasive action of material can be reduced to the full extent, avoid the dimensional discrepancy problem of wearing and tearing and bringing, fully meet the request for utilization of aeronautical product.
Accompanying drawing explanation
The structural representation of this type of vibration measurement device of Fig. 1 tradition.
Fig. 2 is the structural representation of vibration measurement device one preferred embodiment of the present invention.
Embodiment
Below just accompanying drawing in conjunction with the embodiments, is described in further detail the specific embodiment of the present invention, is easier to understand, grasp to make technical solution of the present invention.
The present invention's innovation proposes a kind of high precision magneto-electric aviation vibration measurement device, and the high precision being intended to solve vibration measurement device maintains problem.Its technical solution as shown in Figure 2, this kind of high precision magneto-electric aviation vibration measurement device, be made up of column jecket 5, magnetic steel component 2, coil block 3 and spring 4, this magnetic steel component 2 is connected in column jecket 5 and the axle 21 at magnetic steel component 2 two ends is all arranged with spring 4, and above-mentioned coil block 3 location is secured to outside column jecket 5.Main architectural feature: the both ends of this column jecket 5 are all equipped with the bearing block assembly 6 be made up of rigidity cover for seat and ball bearing 62 attaching, wherein rigidity cover for seat connects fixing and rigidity cover for seat middle inside radial direction is provided with round bottom groove with column jecket 5, this ball bearing 62 is provided with axle sleeve and radially-arranged three balls 621, and ball 621 abuts in round bottom groove, axle 21 cross-under of magnetic steel component is positioned in axle sleeve.
As further refinement and the optimization of such scheme, this ball bearing 62 to be provided with the roller of end face rolling friction between two between ball.
Above-mentioned rigidity cover for seat is split socket joint type structure, comprises the abutting block 612 of shell 611 and interior band round bottom groove thereof, abuts between block 612 and shell 11 and is provided with elasticity fitting 613.
Under this structure: utilize three uniform ball bearing position control oscillatory system accurately main bodys to move along axis all the time, can not offset.During oscillatory system bulk motion, position control accurately can ensure that three's mean allocation is moved the sliding friction produced, drive three uniform balls to move simultaneously, the damping of abundant reduction oscillatory system, the abrasive action of material can be reduced to the full extent, avoid the dimensional discrepancy problem of wearing and tearing and bringing, make one-piece construction can keep mated condition closely in the moving back and forth of high strength, ensure that the precision of overall measurement mechanism, avoid the problem of the proving installation accuracy decline caused because of kernel component wearing and tearing, ensure that the high reliability of Long-Time Service simultaneously, fully meet the request for utilization of aeronautical product.
Detailed description to sum up for this device is visible, compare to traditional vibration measurement device, this vibration measurement device compact conformation, light and handy, stable connection, can reduce the abrasive action of material to the full extent, avoid the dimensional discrepancy problem of wearing and tearing and bringing, fully meet the request for utilization of aeronautical product.
In addition to the implementation, the present invention can also have other embodiment.All employings are equal to the technical scheme of replacement or equivalent transformation formation, all drop within the present invention's scope required for protection.
Claims (3)
1. a high precision magneto-electric aviation vibration measurement device, by column jecket, magnetic steel component, coil block and spring are formed, described magnetic steel component is connected in column jecket and the axle at magnetic steel component two ends is all arranged with spring, described coil block location is secured to outside column jecket, it is characterized in that: the both ends of described column jecket are all equipped with the bearing block assembly be made up of rigidity cover for seat and ball bearing attaching, wherein said rigidity cover for seat connects fixing with column jecket and rigidity cover for seat middle inside radial direction is provided with round bottom groove, described ball bearing is provided with axle sleeve and radially-arranged three balls, and ball abuts in round bottom groove, the axle cross-under of magnetic steel component is positioned in axle sleeve.
2. high precision magneto-electric aviation vibration measurement device according to claim 1, is characterized in that: described ball bearing to be provided with the roller of end face rolling friction between two between ball.
3. high precision magneto-electric aviation vibration measurement device according to claim 1, is characterized in that: described rigidity cover for seat is split socket joint type structure, comprises the abutting block of shell and interior band round bottom groove thereof, abuts between block and shell and is provided with elasticity fitting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510960675.5A CN105509870A (en) | 2015-12-21 | 2015-12-21 | High-precision magneto-electric vibration measurement device for aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510960675.5A CN105509870A (en) | 2015-12-21 | 2015-12-21 | High-precision magneto-electric vibration measurement device for aviation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105509870A true CN105509870A (en) | 2016-04-20 |
Family
ID=55718019
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510960675.5A Pending CN105509870A (en) | 2015-12-21 | 2015-12-21 | High-precision magneto-electric vibration measurement device for aviation |
Country Status (1)
| Country | Link |
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| CN (1) | CN105509870A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110987152A (en) * | 2019-11-27 | 2020-04-10 | 苏州长风航空电子有限公司 | High-precision magnetoelectric vibration measuring device for aviation |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3878504A (en) * | 1973-09-21 | 1975-04-15 | Hall Sears Inc | Damped geophone |
| US4504932A (en) * | 1982-02-08 | 1985-03-12 | Metrix Instrument Co. | Geophone having a non-conductive coilform |
| CN2439033Y (en) * | 2000-04-25 | 2001-07-11 | 西安石油勘探仪器总厂 | Eddy-current accelerator seismic detector |
| EP1249714A2 (en) * | 2001-04-09 | 2002-10-16 | Input/Output, Inc. | Double-ended geophone |
| CN201241915Y (en) * | 2008-07-10 | 2009-05-20 | 邹建军 | Rolling bearing for guide rail |
| CN201331587Y (en) * | 2008-12-09 | 2009-10-21 | 重庆地质仪器厂 | Core body for 1HZ detector |
| CN201680903U (en) * | 2010-04-29 | 2010-12-22 | 三门峡上阳电器平衡机械有限公司 | High sensitivity sensor for dynamic balancing machine |
| CN102023309A (en) * | 2010-10-29 | 2011-04-20 | 谭成忠 | Maglev electromagnetic induction cymoscope |
| CN102175304A (en) * | 2011-01-26 | 2011-09-07 | 夏惠兴 | Multi-dimensional vibration sensor |
| CN204255491U (en) * | 2014-11-21 | 2015-04-08 | 九江精密测试技术研究所 | A kind of transient equilibrium electrical measurement vibrating sensing apparatus |
-
2015
- 2015-12-21 CN CN201510960675.5A patent/CN105509870A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3878504A (en) * | 1973-09-21 | 1975-04-15 | Hall Sears Inc | Damped geophone |
| US4504932A (en) * | 1982-02-08 | 1985-03-12 | Metrix Instrument Co. | Geophone having a non-conductive coilform |
| CN2439033Y (en) * | 2000-04-25 | 2001-07-11 | 西安石油勘探仪器总厂 | Eddy-current accelerator seismic detector |
| EP1249714A2 (en) * | 2001-04-09 | 2002-10-16 | Input/Output, Inc. | Double-ended geophone |
| CN201241915Y (en) * | 2008-07-10 | 2009-05-20 | 邹建军 | Rolling bearing for guide rail |
| CN201331587Y (en) * | 2008-12-09 | 2009-10-21 | 重庆地质仪器厂 | Core body for 1HZ detector |
| CN201680903U (en) * | 2010-04-29 | 2010-12-22 | 三门峡上阳电器平衡机械有限公司 | High sensitivity sensor for dynamic balancing machine |
| CN102023309A (en) * | 2010-10-29 | 2011-04-20 | 谭成忠 | Maglev electromagnetic induction cymoscope |
| CN102175304A (en) * | 2011-01-26 | 2011-09-07 | 夏惠兴 | Multi-dimensional vibration sensor |
| CN204255491U (en) * | 2014-11-21 | 2015-04-08 | 九江精密测试技术研究所 | A kind of transient equilibrium electrical measurement vibrating sensing apparatus |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110987152A (en) * | 2019-11-27 | 2020-04-10 | 苏州长风航空电子有限公司 | High-precision magnetoelectric vibration measuring device for aviation |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160420 |
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| RJ01 | Rejection of invention patent application after publication |