CN210533385U - Micro inertial measurement unit - Google Patents
Micro inertial measurement unit Download PDFInfo
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- CN210533385U CN210533385U CN201921437946.9U CN201921437946U CN210533385U CN 210533385 U CN210533385 U CN 210533385U CN 201921437946 U CN201921437946 U CN 201921437946U CN 210533385 U CN210533385 U CN 210533385U
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- 238000005259 measurement Methods 0.000 title claims abstract description 30
- 230000010365 information processing Effects 0.000 claims abstract description 13
- 230000001133 acceleration Effects 0.000 claims abstract description 6
- 229920002379 silicone rubber Polymers 0.000 claims description 8
- 239000004945 silicone rubber Substances 0.000 claims description 6
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
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- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
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Abstract
The present disclosure relates to a micro inertial measurement unit, comprising: the sensor circuit comprises a sensor plate, an information processing plate and an interface plate, wherein the sensor plate, the information processing plate and the interface plate are communicated through flexible connection, a micromechanical gyroscope used for sensing the angular velocity of a carrier and a micromechanical accelerometer used for sensing the acceleration of the carrier are arranged on the sensor plate, and the sensor plate is not directly contacted with the support. The utility model has the advantages that: the structure is simple, the mechanical stress of the micromechanical gyroscope is reduced by directly bonding the micromechanical gyroscope with the bracket, the micromechanical gyroscope is suitable for a phi 40mm micro inertial measurement unit which is an important part of a guided grenade, and the missile attitude measurement function can be realized by using the minimum hardware scale by adopting the micro-integration technology.
Description
Technical Field
The utility model relates to a miniature be used to group.
Background
With the development of miniature missiles such as guided grenades and the like, the miniature inertial set is used as an important component of the missiles, the guidance performance of the missiles is determined by the measurement performance of the miniature inertial set, the size of the missiles is limited by the structural size of the miniature inertial set, and the reliability of the missiles is influenced by the stability of the miniature inertial set, so that the miniature inertial set also has to keep pace with the development steps of the missiles. The micro inertial measurement unit aims to solve the problem of restricting the development of the micro inertial measurement unit, and firstly solves the problems of structural size and large interference of a micro mechanical gyroscope under a vibration condition. The system requires structural arrangement in a narrow space within the range of phi 40mm multiplied by 23mm, and the interference of the micro-mechanical gyroscope in the prior art is large under the vibration condition.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a miniature be used to group provides, its interference of effectively solving under the vibration condition micromechanical gyroscope is big problem partially.
In order to solve the technical problem, the utility model discloses a technical scheme is: a micro inertial measurement unit, comprising: the sensor circuit comprises a sensor plate, an information processing plate and an interface plate, wherein the sensor plate, the information processing plate and the interface plate are communicated through flexible connection, a micromechanical gyroscope used for sensing the angular velocity of a carrier and a micromechanical accelerometer used for sensing the acceleration of the carrier are arranged on the sensor plate, and the sensor plate is not directly contacted with the support.
Compared with the prior art, the utility model discloses following profitable technological effect has:
the device is simple in structure and comprises a support and a sensitive element circuit, wherein the sensitive element circuit is composed of a sensitive element plate, an information processing plate and an interface plate, the sensitive element plate, the information processing plate and the interface plate are communicated through flexible connection, a micromechanical gyroscope and a micromechanical accelerometer are arranged on the sensitive element plate and used for sensing the angular velocity of a carrier, and the sensitive element plate is not directly contacted with the support. The mechanical stress of the micromechanical gyroscope is reduced by directly bonding the micromechanical gyroscope with the bracket, the micromechanical gyroscope is suitable for a phi 40mm miniature inertial measurement unit which is an important part of a guided grenade, and the missile attitude measurement function can be realized by using the minimum hardware scale by adopting the micro-integration technology.
Drawings
FIG. 1 is a schematic structural diagram of a micro inertial measurement unit according to the present invention;
fig. 2 is a top view of the structure shown in fig. 1.
Schematic of the reference numerals
11-sensitive element circuit 12-silicon rubber 13-bracket 15-connecting wire
Detailed Description
The present invention will be described in further detail with reference to specific embodiments, but these examples are only illustrative and do not limit the scope of the present invention.
Referring to fig. 1 and 2, the micro inertial measurement unit of the present invention includes: the device comprises a support 13 and a sensitive element circuit 11, wherein the sensitive element circuit 11 is composed of a sensitive element plate, an information processing plate and an interface plate, the sensitive element plate, the information processing plate and the interface plate are communicated through flexible connection, a micromechanical gyroscope and a micromechanical accelerometer are arranged on the sensitive element plate and used for sensing the angular velocity of a carrier, and the sensitive element plate is not directly contacted with the support.
In one embodiment, the sensor board includes: an X-axis gyro plate, a Y-axis gyro plate, a Z-axis gyro and an accelerometer plate.
In one embodiment, the flexible connection is, for example, by way of a connection line 15.
In one embodiment, the micromechanical gyroscope of the X-axis gyroscope board is embedded inside the support and glued to the support 13 with silicone rubber 12.
In one embodiment, the micromechanical gyroscope of the Y-axis gyroscope board is embedded inside the frame and glued to the frame 13 with silicone rubber 12.
In one embodiment, the micromechanical gyroscope of the Z-axis gyroscope board is embedded inside the support and glued to the support 13 with silicone rubber 12.
In one embodiment, the support 13 is provided with an outer circumferential connection 17.
In one embodiment, the system is installed in the system structure through a threaded hole on the outer circle connecting part.
In one embodiment, the micro inertial measurement unit size is Φ 40mm × 23 mm.
As specific embodiment, the utility model discloses a miniature inertial unit mainly comprises support, sensing element circuit, and the sensing element circuit comprises 3 sensing element boards and an information processing board and a board interface board, and through the flexible coupling communication between them, the angular velocity of micromechanical gyroscope sensitive carrier on the sensing element board, the acceleration of micromechanical accelerometer sensitive carrier to this measurement function that reaches miniature inertial unit, its installation must safe and reliable, and the sensing element board can not have mechanical stress when installing, otherwise can influence the sensing element precision. Therefore, the three micromechanical gyros on the three sensitive element plates are directly adhered to the bracket by glue, and the sensitive element plates are not directly contacted with the bracket. By the aid of the glued sensitive elements, mechanical stress can be effectively reduced, anti-interference capacity is improved, measurement errors are greatly reduced, and measurement accuracy of the micro inertial measurement unit is improved. The micro inertial measurement unit is installed in the system structure body through eight threaded holes in the excircle of the support, and the installation is convenient and reliable.
As specific embodiment, the utility model discloses a miniature group of being used mainly by the support, the sensing element circuit is constituteed, the sensing element circuit mainly comprises X axle top board, Y axle top board, Z axle top and accelerometer board, external interface board, FPG board etc. through the flexonics communication between each board, 3 sensing element boards, X axle top board, Y axle top board, Z axle top and accelerometer board promptly, inside its top embedding support to glue firmly on the support with silicon rubber, so that the sensing element is direct not with support rigid contact. The angular velocity of the sensitive carrier of the micromechanical gyroscope and the acceleration of the sensitive carrier of the micromechanical accelerometer on the sensitive element plate achieve the measuring function of the micro-inertial set, the installation of the micro-inertial set is safe and reliable, the sensitive element plate cannot have mechanical stress when being installed, otherwise, the precision of the sensitive element is influenced, and the mechanical stress can be effectively reduced, the anti-interference capability is improved, the measuring error is greatly reduced, and the measuring precision of the micro-inertial set is improved through the glued sensitive element. The micro inertial measurement unit is installed in the system structure body through eight threaded holes in the excircle of the support, and the installation is convenient and reliable.
Test of
The micro inertial measurement unit forms a real object, is applied to a certain micro missile for verification, participates in multiple flight tests, and has excellent performance in the test process. Compared with the conventional micro-mechanical inertial set, the micro-mechanical inertial set has the advantages of greatly reduced volume and greatly enhanced vibration environment resistance.
The utility model discloses accomplish on phi 40mm 23 mm's little volume and be used to survey the design of combination, realize angular velocity, acceleration measurement function, and output measurement information gives and plays the computer, with minimum circuit scale and structural style satisfy and play and go up the measurement needs, and through using PCB rigid flex board design to make the structure compacter reliable, adopt the direct mode that bonds with the support of micromechanical gyroscope to reduce micromechanical gyroscope's mechanical stress, improve the anti-jamming ability of micromechanical gyroscope under the vibration condition, make product environmental suitability stronger. The inertial measurement unit has the advantages of superior performance in similar products, small volume, light weight, high reliability, strong vibration resistance and the like, has good application prospect and military significance in the field of precise weapon guidance control, and has domestic technical advancement.
The utility model discloses following profitable technological effect has:
the device is simple in structure and comprises a support and a sensitive element circuit, wherein the sensitive element circuit is composed of a sensitive element plate, an information processing plate and an interface plate, the sensitive element plate, the information processing plate and the interface plate are communicated through flexible connection, a micromechanical gyroscope and a micromechanical accelerometer are arranged on the sensitive element plate and used for sensing the angular velocity of a carrier, and the sensitive element plate is not directly contacted with the support. The mechanical stress of the micromechanical gyroscope is reduced by directly bonding the micromechanical gyroscope with the bracket, the micromechanical gyroscope is suitable for a phi 40mm miniature inertial measurement unit which is an important part of a guided grenade, and the missile attitude measurement function can be realized by using the minimum hardware scale by adopting the micro-integration technology.
Although the preferred embodiments of the present invention have been disclosed above, the present invention is not limited thereto. It is obvious that not all embodiments need be, nor cannot be exhaustive here. Any person skilled in the art can change and modify the research scheme of the present invention by adopting the design and content of the above disclosed embodiments without departing from the spirit and scope of the present invention, and therefore, any simple modification, parameter change and modification of the above embodiments by the research entity of the present invention all belong to the protection scope of the scheme of the present invention.
Claims (8)
1. A micro inertial measurement unit, comprising: the sensor circuit comprises a sensor plate, an information processing plate and an interface plate, wherein the sensor plate, the information processing plate and the interface plate are communicated through flexible connection, a micromechanical gyroscope used for sensing the angular velocity of a carrier and a micromechanical accelerometer used for sensing the acceleration of the carrier are arranged on the sensor plate, and the sensor plate is not directly contacted with the support.
2. The micro inertial mass spectrometer of claim 1, wherein the sensor plate comprises: an X-axis gyro plate, a Y-axis gyro plate, a Z-axis gyro and an accelerometer plate.
3. The micro inertial mass according to claim 2, characterized in that the micromechanical gyroscope of the X-axis gyroscope plate is embedded inside the support and glued to the support with silicone rubber.
4. The micro inertial mass according to claim 3, characterized in that the micromechanical gyroscope of the Y-axis gyroscope plate is embedded inside the support and glued to the support with silicone rubber.
5. The micro inertial mass according to claim 2, characterized in that the micromechanical gyroscope of the Z-axis gyroscope plate is embedded inside the support and glued to the support with silicone rubber.
6. The micro inertial measurement unit of claim 1, wherein the support is provided with an outer cylindrical connection part.
7. The micro inertial measurement unit according to claim 6, characterized in that it is mounted in the system structure body by means of a threaded hole on the external cylindrical connection part.
8. The micro inertial mass according to claim 1, characterized in that the micro inertial mass dimensions are Φ 40mm x 23 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921437946.9U CN210533385U (en) | 2019-08-30 | 2019-08-30 | Micro inertial measurement unit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921437946.9U CN210533385U (en) | 2019-08-30 | 2019-08-30 | Micro inertial measurement unit |
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| CN210533385U true CN210533385U (en) | 2020-05-15 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110530351A (en) * | 2019-08-30 | 2019-12-03 | 贵州航天控制技术有限公司 | A kind of miniature used group |
| CN112146651A (en) * | 2020-09-25 | 2020-12-29 | 上海航天控制技术研究所 | Micro-mechanical gyroscope assembly with small volume, low power consumption and high reliability |
-
2019
- 2019-08-30 CN CN201921437946.9U patent/CN210533385U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110530351A (en) * | 2019-08-30 | 2019-12-03 | 贵州航天控制技术有限公司 | A kind of miniature used group |
| CN112146651A (en) * | 2020-09-25 | 2020-12-29 | 上海航天控制技术研究所 | Micro-mechanical gyroscope assembly with small volume, low power consumption and high reliability |
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