CN112067229A - Center-loaded large-size unidirectional force piezoelectric sensor - Google Patents
Center-loaded large-size unidirectional force piezoelectric sensor Download PDFInfo
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- CN112067229A CN112067229A CN202010959950.2A CN202010959950A CN112067229A CN 112067229 A CN112067229 A CN 112067229A CN 202010959950 A CN202010959950 A CN 202010959950A CN 112067229 A CN112067229 A CN 112067229A
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- 239000013078 crystal Substances 0.000 claims abstract description 42
- 238000012360 testing method Methods 0.000 abstract description 16
- 238000005259 measurement Methods 0.000 abstract description 13
- 238000013461 design Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 235000012431 wafers Nutrition 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/16—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force
- G01L5/167—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring several components of force using piezoelectric means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- Engineering & Computer Science (AREA)
- Fluid Mechanics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention discloses a center-loaded large-size unidirectional force piezoelectric sensor, and particularly relates to the technical field of sensing, measurement and control. A large-size unidirectional force piezoelectric sensor loaded in the center comprises an upper cover and a lower cover detachably connected with the upper cover, wherein plug-in holes communicated with each other are formed in the centers of the upper cover and the lower cover and are matched with a rigid supporting rod, a plurality of piezoelectric crystal boxes are distributed between the upper cover and the lower cover, unit crystal groups are arranged in the piezoelectric crystal boxes, a fixing tray is arranged on the lower cover, and the fixing tray is detachably connected to the rigid supporting rod. The technical scheme of the invention solves the problem that the existing sensor can not meet the measurement requirement of the dynamic aerodynamic force of the aircraft model under the specific test condition, and can be used for the impulse wind tunnel force measurement of the aircraft model.
Description
Technical Field
The invention relates to the technical field of sensing, measurement and control, in particular to a center-loaded large-size unidirectional force piezoelectric sensor.
Background
A large number of wind tunnel tests are required to be carried out in aircraft development, aerodynamic load characteristic curves of the aircraft are obtained, and more accurate test data are provided for the aircraft development. When the wind tunnel test is carried out, the aircraft model needs to be supported by the model supporting system, and aerodynamic load borne by the aircraft model in the wind tunnel is measured through the force sensor. At present, most of the existing wind tunnel tests adopt a measurement mode of a built-in sensor, namely, when an aircraft model is designed, designers consider that the sensor is installed inside the aircraft model. Most of force sensors adopted in the current measurement are strain type sensors, and have good static characteristics, but the natural frequency of the force sensors is usually low, and the application requirement of the dynamic aerodynamic force measurement of an aircraft model under a specific test condition cannot be met.
Disclosure of Invention
The invention aims to provide a center-loaded large-size unidirectional force piezoelectric sensor, and solves the problem that the conventional sensor cannot meet the dynamic aerodynamic force measurement requirement of an aircraft model under a specific test condition.
In order to achieve the purpose, the technical scheme of the invention is as follows: a large-size unidirectional force piezoelectric sensor loaded in the center comprises an upper cover and a lower cover detachably connected with the upper cover, wherein plug-in holes communicated with each other are formed in the centers of the upper cover and the lower cover and are matched with a rigid supporting rod, a plurality of piezoelectric crystal boxes are distributed between the upper cover and the lower cover, unit crystal groups are arranged in the piezoelectric crystal boxes, a fixing tray is arranged on the lower cover, and the fixing tray is detachably connected to the rigid supporting rod.
The principle and the effect of the technical scheme are as follows: when measuring, fix this sensor on rigidity branch with the help of fixed tray, and rigidity branch is used for supporting the aircraft model, and the aerodynamic force that the aircraft model bore then transmits to the unit crystal assembly through rigidity branch in the test procedure to realize the regulation of aerodynamic force measuring range with the help of the quartzy brilliant box of piezoelectricity and the unit crystal assembly's in it quantity, be convenient for satisfy the different measuring demand of aircraft model, improved the range of application of this sensor.
Further, all the unit crystal groups are connected in series.
Through the arrangement, the measuring range and the sensitivity of the sensor can be enlarged, the number of the unit crystal groups connected in series can be adjusted at any time according to the size of the tested load, and the efficiency and the accuracy of the test are improved.
Further, the unit crystal group adopts XY cutting type.
Through the arrangement, the sensor can be used for measuring the normal load.
Furthermore, the lower cover is provided with a boss matched with the piezoelectric crystal box.
Through the arrangement, the stress area of the sensor can be ensured to be on the crystal box of the piezoelectric sensor.
Furthermore, the central line of the plug hole coincides with the central axis of the rigid supporting rod.
Through the arrangement, the device can measure the tension on the rigid supporting rod all the time, and the accuracy of the measuring result is further improved.
Compared with the prior art, the beneficial effect of this scheme:
1. the scheme adopts the arrangement mode of a plurality of unit crystal groups, realizes the accurate measurement of the spatial six-dimensional force (the six-dimensional force refers to the axial force, the normal force, the lateral force, the rolling moment, the yawing moment and the pitching moment which are borne by the aircraft model in the wind tunnel test, respectively corresponds to the force loads along the directions of the x axis, the y axis and the z axis, and the moment loads around the directions of the x axis, the y axis and the z axis), has the advantages of high test precision and convenient adjustment and installation, and effectively solves the problems of large interference and difficult adjustment of large-mass and long and narrow aircraft models in the wind tunnel test;
2. the sensor is directly connected with the rigid supporting rod for supporting the aircraft model, the sensor does not need to be arranged in the model, the flexibility of design and test is greatly improved, and the sensor and the rigid supporting rod adopt coaxial design, so that the pulling force borne by the supporting rod can be directly measured, and the test error caused by different connection angles of the rigid supporting rod and the model is not needed;
3. in the testing stage, different force-measuring loads can be adapted by adjusting the number of the piezoelectric crystal boxes and the size of the piezoelectric wafers in the crystal boxes, and the whole unidirectional force piezoelectric sensor does not need to be replaced; in addition, the load borne by the plurality of unit crystal groups is tested together through series connection and matching, and the center loading large-size piezoelectric sensor consisting of the plurality of piezoelectric crystal boxes is integrally formed.
Drawings
Figure 1 is an exploded schematic view of a center-loaded large-scale unidirectional force piezoelectric sensor of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
fig. 3 is a schematic structural diagram of a center-loaded large-sized unidirectional force piezoelectric sensor according to the present invention.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the piezoelectric crystal box comprises an upper cover 1, a lower cover 2, a rigid supporting rod 3, a piezoelectric crystal box 4, a unit crystal group 5, a round hole 6, a circular ring 7, a boss 8 and a fixed tray 9.
Examples
As shown in figures 1 and 3: a large-size unidirectional force piezoelectric sensor loaded in the center comprises an upper cover 1 and a lower cover 2 connected with the upper cover 1 through bolts, wherein plug holes communicated with each other are formed in the centers of the upper cover 1 and the lower cover 2, the plug holes are in transition fit with a rigid supporting rod 3, and the center line of each plug hole is overlapped with the center axis of the rigid supporting rod 3. The utility model discloses a piezoelectric crystal box, including upper cover 1, the upper cover has a plurality of screw holes, it has the same piezoelectric crystal box 4 (as shown in figure 2) with screw hole quantity to distribute between upper cover 1 and the lower cover 2, open at the center of piezoelectric crystal box 4 has the through-hole that is linked together with the screw hole, piezoelectric crystal box 4 internally mounted has the unit brilliant group 5 of XY cut type, 3 normal loads of measurable quantity rigidity branch with the help of unit brilliant group 5, all open two round holes 6 on 4 circumferences of every piezoelectric crystal box, be used for later stage welding sensor port through two round holes 6, a plurality of piezoelectric crystal boxes 4 carry out the series connection cooperation through two ports.
Two rings 7 distributed at intervals are welded on the lower cover 2, the ring 7 positioned on the inner side is welded at the edge of the inserting hole, the diameter of the ring 7 positioned on the outer side is the same as that of the upper cover 1, a boss 8 communicated with the through hole is arranged on the lower cover 2 between the two rings 7, an internal thread matched with the threaded hole of the upper cover 1 is arranged in the boss 8, a bolt is connected with the internal thread of the threaded hole and the boss 8 through common threads, the bolt penetrates through the upper cover 1 and the piezoelectric crystal box 4 and is in non-penetrating threaded fit with the internal thread of the lower cover 2, and therefore the piezoelectric crystal box 4 is connected with the upper cover 1 and the lower cover 2 into a whole; the bottom of the lower cover 2 is also connected with a fixed tray 9 through bolts, the fixed tray 9 is connected with the lower end of the rigid supporting rod 3 through threads, and the upper end of the rigid supporting rod 3 supports the aircraft model.
The working process of the scheme is as follows: the sensor is directly connected with the center of the rigid supporting rod 3, and the sensor and the axis of the rigid supporting rod 3 are kept on the same straight line, so that the sensor can measure the tension on the rigid supporting rod 3 all the time, and the accuracy of the measuring result is improved. When measurement is performed, the number of the piezoelectric crystal boxes 4 is determined according to the specific load, in the embodiment, three piezoelectric crystal boxes 4 are adopted, the aerodynamic force borne by the aircraft model in the test process is transmitted to the unit crystal groups 5 through the rigid support rods 3, so that the numerical value measurement is realized by means of the unit crystal groups 5 in the piezoelectric crystal boxes 4, and the adjustment of the aerodynamic force measurement range is realized by installing different numbers of piezoelectric crystal boxes 4, so that different measurement requirements of the aircraft model are met conveniently, and the application range of the sensor is expanded; meanwhile, the sensor does not need to be installed inside an aircraft model, so that the flexibility of design and test is greatly improved, and the whole sensor does not need to be replaced.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (5)
1. A center-loaded large-size unidirectional force piezoelectric sensor is characterized in that: the piezoelectric crystal box comprises an upper cover and a lower cover detachably connected with the upper cover, wherein plug-in holes which are communicated with each other are formed in the centers of the upper cover and the lower cover, the plug-in holes are matched with a rigid supporting rod, a plurality of piezoelectric crystal boxes are distributed between the upper cover and the lower cover, a unit crystal group is arranged in each piezoelectric crystal box, a fixed tray is arranged on the lower cover, and the fixed tray is detachably connected to the rigid supporting rod.
2. A center-loaded large-scale unidirectional force piezoelectric sensor as claimed in claim 1, wherein: all the unit crystal groups are connected in series.
3. A center-loaded large-scale unidirectional force piezoelectric sensor as claimed in claim 1, wherein: the unit crystal group adopts XY cutting type.
4. A center-loaded large-scale unidirectional force piezoelectric sensor as claimed in claim 1, wherein: and the lower cover is provided with a boss matched with the piezoelectric crystal box.
5. A center-loaded large scale uni-directional force piezoelectric transducer according to any of claims 1-4 wherein: the central line of the plug hole is coincided with the central axis of the rigid supporting rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010959950.2A CN112067229A (en) | 2020-09-14 | 2020-09-14 | Center-loaded large-size unidirectional force piezoelectric sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010959950.2A CN112067229A (en) | 2020-09-14 | 2020-09-14 | Center-loaded large-size unidirectional force piezoelectric sensor |
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| Publication Number | Publication Date |
|---|---|
| CN112067229A true CN112067229A (en) | 2020-12-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010959950.2A Pending CN112067229A (en) | 2020-09-14 | 2020-09-14 | Center-loaded large-size unidirectional force piezoelectric sensor |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101430237A (en) * | 2007-11-05 | 2009-05-13 | 中国科学院合肥物质科学研究院 | Multidimensional force test system in vibration experiment |
| CN103278305A (en) * | 2013-05-24 | 2013-09-04 | 南京航空航天大学 | Wind channel model tail support rod structure capable of actively damping vibration |
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| TWM533206U (en) * | 2016-05-12 | 2016-12-01 | Cheng-Yuan Wu | Force sensing fastener |
| CN106441675A (en) * | 2016-11-08 | 2017-02-22 | 烟台职业学院 | Non-load-sharing piezoelectric thrust test device |
| CN106568544A (en) * | 2016-10-18 | 2017-04-19 | 烟台职业学院 | Sheet metal hot stamping force measurement device |
| CN110174205A (en) * | 2019-04-02 | 2019-08-27 | 济南大学 | A kind of joint of robot piezoelectric six-dimensional force sensor and its measurement method |
| CN111024275A (en) * | 2019-12-23 | 2020-04-17 | 大连理工大学 | Shear type unidirectional force piezoelectric sensor |
-
2020
- 2020-09-14 CN CN202010959950.2A patent/CN112067229A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101430237A (en) * | 2007-11-05 | 2009-05-13 | 中国科学院合肥物质科学研究院 | Multidimensional force test system in vibration experiment |
| CN103278305A (en) * | 2013-05-24 | 2013-09-04 | 南京航空航天大学 | Wind channel model tail support rod structure capable of actively damping vibration |
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| TWM533206U (en) * | 2016-05-12 | 2016-12-01 | Cheng-Yuan Wu | Force sensing fastener |
| CN106568544A (en) * | 2016-10-18 | 2017-04-19 | 烟台职业学院 | Sheet metal hot stamping force measurement device |
| CN106441675A (en) * | 2016-11-08 | 2017-02-22 | 烟台职业学院 | Non-load-sharing piezoelectric thrust test device |
| CN110174205A (en) * | 2019-04-02 | 2019-08-27 | 济南大学 | A kind of joint of robot piezoelectric six-dimensional force sensor and its measurement method |
| CN111024275A (en) * | 2019-12-23 | 2020-04-17 | 大连理工大学 | Shear type unidirectional force piezoelectric sensor |
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Application publication date: 20201211 |