CN1326090A - Bidirectionally synthesizing jet gyroscope - Google Patents
Bidirectionally synthesizing jet gyroscope Download PDFInfo
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- CN1326090A CN1326090A CN 01129222 CN01129222A CN1326090A CN 1326090 A CN1326090 A CN 1326090A CN 01129222 CN01129222 CN 01129222 CN 01129222 A CN01129222 A CN 01129222A CN 1326090 A CN1326090 A CN 1326090A
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- jet
- gyroscope
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- synthesizing jet
- angular velocity
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- 230000002194 synthesizing effect Effects 0.000 title claims description 21
- 239000012528 membrane Substances 0.000 claims abstract description 8
- 239000007921 spray Substances 0.000 claims description 22
- 238000012545 processing Methods 0.000 claims description 9
- 238000005516 engineering process Methods 0.000 claims description 7
- 230000003287 optical effect Effects 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 230000001419 dependent effect Effects 0.000 claims description 2
- 230000035945 sensitivity Effects 0.000 abstract description 7
- 238000010438 heat treatment Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 239000012530 fluid Substances 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000005755 formation reaction Methods 0.000 description 4
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 239000002210 silicon-based material Substances 0.000 description 1
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Abstract
A bidirectionally synthesized jet gyroscope for measuring angle speed is disclosed. Two synthesized jet sources, which are fully same but have different speeds are used. Said jet source is formed by vibrating membrane of driver and nozzle. One or more pairs of thermosensitive sensors are symmetrically arranged at both sides of the central line of synthesized jet. Its advantages are simple structure, long service life, low cost, and high sensitivity and resolution.
Description
The invention belongs to sensor technical field.
All need to widely apply angular-rate sensor or gyroscope in fields such as automobile, military affairs, the product for civilian use (such as camera, toy, mouse), Industry Control, aviation and boats and ships.Development performance novel gyroscope better, that reliability is higher, price is lower is the target that people are pursuing always.In the device of the measured angular speed of having used at present, general characteristics are to need rotary part.The existence of rotary part makes that the life-span of device is short, and reliability is low, and in addition, it also makes little processing difficulties, and cost raises.United States Patent (USP) 5012676 has proposed a kind of with the gyroscope of gas jet as actuating medium, and its synoptic diagram as shown in Figure 1.It is with a pump 1,2 form fluid by spout 3 flows, a flow through long and narrow runner 5 and be subjected to the heating of heating plate 4 and form hot fluid of this fluid streams forms jet via spout 6 subsequently, and is mapped on two heat sensitive sensors 8 that are arranged symmetrically on the lumen centerline in cavity 7.When not having angular velocity, jet does not have deflection, two thermo-responsive silks detect identical temperature, and in the time of angular velocity, jet deflects, formation temperature is poor between two heat sensitive sensors, is comprising the information of angular velocity in this difference, can measured angular speed by measuring temperature difference.There is a significant drawback in above-mentioned gyroscope, because jet is only along a direction, when being applied to the situation of non-uniform angular velocity, the deflection of jet is the effect that is subjected to coriolis force and tangential force simultaneously, therefore, include angular velocity omega and angular acceleration in two detected temperature difference of thermo-responsive silk
Information.This means that above-mentioned gyroscope can not get correct angular velocity information when being applied to non-uniform angular velocity situation.In addition, the parts of the key in the above-mentioned gyroscope are pump 1,2 and runner 5, and this structure makes that this gyrostatic size is bigger, on the high side.Simultaneously, long and narrow runner 5 makes the effluxvelocity decay very fast, and this will cause gyrostatic sensitivity and resolution to reduce greatly.
The objective of the invention is to propose a kind of bidirectionally synthesizing jet gyroscope for overcoming the weak point of prior art, it as actuating medium, can reject angular acceleration with gas jet effectively under non-uniform angular velocity situation
Information obtains angular velocity information.Have simple in structure, good reliability, sensitivity and resolution height, characteristics that cost is low simultaneously.
The present invention proposes a kind of bidirectionally synthesizing jet gyroscope, it is characterized in that, adopt two bursts of identical synthesizing jet sources that constitute by driver vibrating membrane and spout that speed is opposite, a pair of or many heat hot dependent sensor is arranged symmetrically in the center line both sides of said synthesizing jet, the position of this heat sensitive sensor is positioned at nozzle diameter 9-15 doubly outside the distance.
The present invention can adopt precision optical machinery processing or micro-processing technology to make.
The driver of said synthetic spray is an electromagnetism, piezoelectricity, any one of type of drive such as static.
Said synthesizing jet source comprises a shell, be fixed on the working cavity on the shell, the synthetic spray that driver vibrating membrane and spout constitute is fixed on the wiring board that has metering circuit of shell and cavity one side, is arranged symmetrically in a plurality of backflows and louvre on the jet working cavity.
Principle of work of the present invention and characteristic:
At first simply introduce the notion of synthetic spray.Fig. 2 is the basic functional principle figure of synthetic spray.A cavity 10 is arranged among the figure, and cavity 10 1 sides are films 9, and opposite side has an aperture (spout) 11, and the mode by film periodic vibration makes gas periodically be entered by aperture and flows out cavity.When gas flows out aperture, effluent air and form a shear layer on every side between the stationary gas, this layer vortex collar vortex 12 of formation of will reeling, it leaves cavity under the effect and moves downstream drawing certainly.Meanwhile, along with the past swivel motion of film, gas will be inhaled into cavity from aperture, and therefore collar vortex is not subjected to the influence of suction process at this moment away from cavity.Like this, a series of collar vortex will form, and these collar vortexs will experience process such as instability and fragmentation and finally form turbulent flow spray 13 near aperture in motion process.This several characteristics that is sprayed with: 1) need not FLUID TRANSPORTATION, clean mass rate is zero; 2) electrical quantity control, the speed of jet can be undertaken by changing the actuator electrical parameter.These characteristics makes synthetic spray can be integrated in easily in the measurement of angular velocity, and it has simplified the pumping unit that general injection stream needs, and can adopt micro-processing technology to process, thereby reduce cost greatly.
The synoptic diagram of bidirectionally synthesizing jet gyroscope measured angular speed as shown in Figure 3.14 is bidirectionally synthesizing jet gyroscope among the figure, F
LBe centrifugal force, F
KBe coriolis force, V
rBe the speed in the relative measured object measuring element, the angular velocity of ω for measuring.Under the uniform angular velocity situation, F
KIn only comprising coriolis force, this moment can obtain ratio in 4 ω * V
rElectric signal, these 2 ω * V than single injection stream
rIncrease and be twice.And under non-uniform angular velocity situation, because F
KIn comprising coriolis force and tangential force, as previously mentioned, folk prescription can't accurately detect to fluidic gyro, and to two sprays of the bidirectionally synthesizing jet gyroscope of this paper, the coriolis force of left side spray
The coriolis force of the right spray is
。Comprehensively have: F=F
KL-F
KR=4 ω * V
rObviously no matter the two sprays by the reverse direction jet under uniform angular velocity and non-uniform angular velocity situation, can both successfully detect angular velocity, and the gyroscope of comparing single injection stream simultaneously can increase one times of sensitivity.
Bidirectionally synthesizing jet gyroscope utilizes above-mentioned principle and forms in conjunction with synthetic spray notion.Owing to do not have pump and long and narrow runner, this gyroscope can adopt dual mode to machine, the one, and precision optical machinery processing, the 2nd, micromachined is just processed through the IC technology with silicon materials.It produces jet by synthetic spray and is used as actuating medium, is not having under the situation of angular velocity, and jet can not deflect, as shown in Figure 4.In this time, a pair of or many heat sensitive sensors to heating that are arranged symmetrically in the jet will be subjected to the same impact of the air-flow of relative low temperature, so temperature is identical, does not have electric signal output.In the time of angular velocity, owing to be subjected to the coriolis force effect, jet deflects, and synoptic diagram as shown in Figure 5.At this time, the jet impulse generation difference that corresponding a pair of heat sensitive sensor is suffered, temperature difference will produce between these two sensors, and it is stressed that this temperature difference is proportional to jet, and jet is comprising the information of angular velocity in stressed, therefore by measuring the information that temperature difference can obtain angular velocity.
Characteristics of the present invention and range of application:
1, adopt two spray correlation, can measure uniform angular velocity and non-uniform angular velocity, sensitivity is compared single injection stream gyro and is increased and be twice.
2, owing to adopt synthetic spray apparatus as jet source, adopt fluid as actuating medium, do not have rotary part, therefore this gyrostatic mission life is longer.
3, adopt synthetic spray to form jet, do not have long and narrow runner, simple in structure, be convenient to processing and manufacturing;
4, jet acts directly on the Sensitive Apparatus, and effluxvelocity is bigger, so sensitivity and resolution height.
5, because the micro-processing technology maturation of synthetic spray and heat sensitive sensor can be utilized the technology of making integrated circuit
(IC technology) is a large amount of to be made, and greatly reduces cost, therefore is applicable to situation cheaply, than
As be used for airbag safety systems and toy in the automobile;
6, the present invention is suitable for the long-life feelings of needs of the application under the different occasions, particularly work under bad environment
Condition.
Brief Description Of Drawings:
Fig. 1 is the structural representation of existing fluidic gyro.
Fig. 2 is the principle of work synoptic diagram of synthetic spray of the present invention.
Fig. 3 is an angular velocity measurement principle schematic of the present invention.
Fig. 4 is not left-right symmetric figure for there being the angular velocity jet in the present invention.
Fig. 5 is for there being the angular velocity jet figure that deflects in the present invention.
Fig. 6 is the structure meter synoptic diagram of the embodiment one of use pair of sensors of the present invention.
Fig. 7 is the structural representation of the embodiment two of two pairs of sensors of use of the present invention.
The present invention designs two kinds of bidirectionally synthesizing jet gyroscope embodiment, is described with reference to the accompanying drawings as follows:
Embodiment one is for having the bidirectionally synthesizing jet gyroscope of a pair of temperature sensor, and its structure as shown in Figure 6.The right and left is symmetrical fully along the vibrating membrane center line among the figure, and half describes with the left side here.Package casing 15 can be cylindrical or square, and jet working cavity 18 is fixed on the shell 15, one side the jet working cavity be the wiring board 16 that has metering circuit, it is fixed on shell 15 and the jet working cavity 18.Arrange laterally zygomorphic synthetic spray on jet working cavity 18 right sides, they are made of driver vibrating membrane 21 and synthetic spray chamber body 22 and spout 20.The driver of vibrating membrane 21 can adopt Piezoelectric Driving, static driven or Electromagnetic Drive, and wherein the amplitude of Electromagnetic Drive can be bigger, helps the formation of high effluxvelocity, and the driver of vibrating membrane adopts Electromagnetic Drive among the embodiment one, and frequency of operation is 500Hz.The size of spout 20 can be weighed selection as required, in general, under the identical condition of semiperiod mean mass flux, the sensitivity of the turn meter of small size orifice design and resolution will be higher than the design of large scale spout, nozzle diameter among the embodiment one is 0.5mm, and vibration film 21a and 21b distance center line height are 1mm.In order to detect jet, be that two temperature sensor 19a and the 19b that line of symmetry is arranged is fixed on the jet working cavity with spout 20 center lines, its distance to spout 20 is 10 times nozzle diameter in embodiment one, is 5mm apart from spout just.Temperature sensor adopts the heating thermistor wire to constitute, and its temperature is than jet temperature height.In order effectively to form jet and to prevent that temperature raise in the cavity 18, four backflows and louvre 17a-17d are arranged symmetrically in respectively on the jet working cavity 18, and wherein two on the left side of heating thermistor wire, and two are arranged in the right.Working cavity length in embodiment one is taken as 10mm, highly is 5mm, and backflow and heat radiation aperture are 0.2mm.
Said apparatus mainly is to produce jet by the synthetic sprays by 21,22 and 20 formations, is not having under the situation of angular velocity, and jet can not deflect.In this time, the heat sensitive sensor that is arranged symmetrically in a pair of heating in the jet will be subjected to the same impact of the air-flow of relative low temperature, because temperature is identical, not have electric signal output.In the time of angular velocity, because the coriolis force effect, jet deflects.At this time, the jet impulse generation difference that a pair of temperature sensor is suffered, temperature difference will produce between two sensors, and this temperature difference is proportional to coriolis force, and comprising the information of angular velocity in the coriolis force, therefore by measuring the information that temperature difference can obtain angular velocity.
Except a pair of temperature sensor shown in Figure 6 is arranged, embodiment two is for having the bidirectionally synthesizing jet gyroscope of two pairs of temperature sensors, its structure as shown in Figure 7, temperature sensor is respectively 19a-19d among the figure, other structures and Fig. 6 are basic identical, principle of work is also basic identical, but accuracy of detection is higher.One side working cavity length among the embodiment two is taken as 9mm, highly be 4mm, backflow and heat radiation aperture are 0.2mm, the driver of vibration film is a Piezoelectric Driving, vibration frequency is 2000Hz, and nozzle diameter is 0.3mm, and vibration film 21a and 21b distance center line height are 0.5mm, temperature sensor is 14 times a nozzle diameter apart from the distance of spout, just 5.2mm.
Except that above two embodiment, can also adopt manyly to the sensor symmetric arrangement, will help improving accuracy of detection like this, reduce error.
Claims (4)
1. bidirectionally synthesizing jet gyroscope, it is characterized in that, adopt two bursts of identical synthesizing jet sources that constitute by driver vibrating membrane and spout that speed is opposite, a pair of or many heat hot dependent sensor is arranged symmetrically in the center line both sides of said synthesizing jet, the position of this heat sensitive sensor is positioned at nozzle diameter 9-15 doubly outside the distance.
2. bidirectionally synthesizing jet gyroscope as claimed in claim 1 is characterized in that, adopts precision optical machinery processing or micro-processing technology to make.
3. bidirectionally synthesizing jet gyroscope as claimed in claim 1 is characterized in that, the driver of said synthetic spray is an electromagnetism, piezoelectricity, any one of type of drive such as static.
4. bidirectionally synthesizing jet gyroscope as claimed in claim 1, it is characterized in that, said synthesizing jet source comprises a shell, be fixed on the working cavity on the shell, the synthetic spray that driver vibrating membrane and spout constitute, be fixed on the wiring board that has metering circuit of shell and cavity one side, be arranged symmetrically in a plurality of backflows and louvre on the jet working cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB011292229A CN1153046C (en) | 2001-06-15 | 2001-06-15 | Bidirectionally synthesizing jet gyroscope |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB011292229A CN1153046C (en) | 2001-06-15 | 2001-06-15 | Bidirectionally synthesizing jet gyroscope |
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| Publication Number | Publication Date |
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| CN1326090A true CN1326090A (en) | 2001-12-12 |
| CN1153046C CN1153046C (en) | 2004-06-09 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100371716C (en) * | 2004-11-25 | 2008-02-27 | 清华大学 | Micro-channel fluid angular rate sensor |
| CN102645212A (en) * | 2012-04-27 | 2012-08-22 | 清华大学 | Micro thermal drive airflow gyro and manufacture method thereof |
| CN112762919A (en) * | 2020-12-29 | 2021-05-07 | 吉林大学 | Liquid piezoelectric jet gyroscope based on electrochemical energy conversion and measuring method |
| CN114353777A (en) * | 2022-01-10 | 2022-04-15 | 长春汽车工业高等专科学校 | Piezoelectric synthesis jet gyroscope for balancing aircraft |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100409134C (en) * | 2006-04-11 | 2008-08-06 | 东南大学 | Jet speed control device for microjet gyroscope |
-
2001
- 2001-06-15 CN CNB011292229A patent/CN1153046C/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100371716C (en) * | 2004-11-25 | 2008-02-27 | 清华大学 | Micro-channel fluid angular rate sensor |
| CN102645212A (en) * | 2012-04-27 | 2012-08-22 | 清华大学 | Micro thermal drive airflow gyro and manufacture method thereof |
| CN102645212B (en) * | 2012-04-27 | 2014-11-26 | 清华大学 | Micro thermal drive airflow gyro and manufacture method thereof |
| CN112762919A (en) * | 2020-12-29 | 2021-05-07 | 吉林大学 | Liquid piezoelectric jet gyroscope based on electrochemical energy conversion and measuring method |
| CN112762919B (en) * | 2020-12-29 | 2022-11-08 | 吉林大学 | Liquid piezoelectric jet gyroscope based on electrochemical energy conversion and measuring method |
| CN114353777A (en) * | 2022-01-10 | 2022-04-15 | 长春汽车工业高等专科学校 | Piezoelectric synthesis jet gyroscope for balancing aircraft |
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| CN1153046C (en) | 2004-06-09 |
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