CN114353793B - Vibration reduction mounting plate applied to sensitive device - Google Patents
Vibration reduction mounting plate applied to sensitive device Download PDFInfo
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- CN114353793B CN114353793B CN202210263214.2A CN202210263214A CN114353793B CN 114353793 B CN114353793 B CN 114353793B CN 202210263214 A CN202210263214 A CN 202210263214A CN 114353793 B CN114353793 B CN 114353793B
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- 230000009467 reduction Effects 0.000 title claims description 20
- 238000013016 damping Methods 0.000 claims abstract description 45
- 229920006324 polyoxymethylene Polymers 0.000 claims description 12
- 238000001746 injection moulding Methods 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims 2
- 229920009382 Polyoxymethylene Homopolymer Polymers 0.000 claims 1
- 230000003044 adaptive effect Effects 0.000 claims 1
- 230000008859 change Effects 0.000 abstract description 7
- 230000017525 heat dissipation Effects 0.000 abstract description 6
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 238000013461 design Methods 0.000 abstract description 4
- 230000002238 attenuated effect Effects 0.000 abstract description 2
- 238000012545 processing Methods 0.000 abstract description 2
- 238000012360 testing method Methods 0.000 description 27
- 238000000034 method Methods 0.000 description 8
- 239000000306 component Substances 0.000 description 6
- 238000009434 installation Methods 0.000 description 6
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- WSFSSNUMVMOOMR-UHFFFAOYSA-N Formaldehyde Chemical compound O=C WSFSSNUMVMOOMR-UHFFFAOYSA-N 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 238000001845 vibrational spectrum Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
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- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000000741 silica gel Substances 0.000 description 2
- 229910002027 silica gel Inorganic materials 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
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Abstract
The invention relates to a vibration damping mounting plate applied to a sensitive device, belonging to the technical field of vibration damping structures of sensitive devices. The invention has the advantages that: the high-frequency small-amplitude vibration can be attenuated, the heat dissipation of the device can be facilitated, and the influence of temperature change on the IMU is effectively avoided; and the structure design is simple, the processing and the production are convenient, and the application field is wide.
Description
Technical Field
The invention relates to the technical field of vibration reduction structures of sensitive devices, in particular to a vibration reduction mounting plate of an inertial navigation system based on polyformaldehyde and a preparation method thereof.
Background
The inertial navigation system has the advantages of capability of providing position, speed, course and attitude angle data, good navigation information continuity, low noise, good short-term precision and stability and the like, and is widely applied to military and civil navigation systems of aerocrafts such as airplanes, missiles, rockets and the like, ships and warships and the like.
An IMU (Inertial measurement Unit, IMU) is a core component of an Inertial navigation system, and is composed of a gyroscope and an accelerometer, these components are very sensitive to vibration and temperature, and a large amount of data shows that temperature variation and high-frequency vibration are important factors influencing measurement values of the IMU. But during actual use, vibration and temperature variation are unavoidable. However, the IMU sensor has light weight, small volume and high requirement on the vibration environment, so the design of the vibration damping structure is always a design difficulty. According to data analysis, the impact sensitive area of an Inertial Measurement Unit (IMU) is about 10kHz at high frequency, high-frequency impact stress waves and impact energy need to be effectively attenuated, and otherwise, secondary damage of the impact stress waves can be caused.
Most of vibration damping devices applied to inertial navigation systems and disclosed in the prior art are complex in structure or troublesome to install, and rubber vibration damping pads are adopted between the IMU and the support in the technical disclosure, so that the vibration damping pads are good in isolation effect on medium-high frequency small-amplitude vibration, but are used in an internal installation mode more, suitable for small-size devices and not beneficial to heat dissipation.
Therefore, how to reduce the influence of low-frequency large-amplitude vibration on the inertial component of the IMU and improve the measurement accuracy of the inertial component is always the focus of research in the field of inertial navigation. Chinese patent No. CN111016033B discloses "an IMU vibration-damping and heat-insulating device based on silica gel and a method for manufacturing the same", which is improved in structure compared with the previously disclosed complex vibration-damping structure combining other machines with silica gel, but the structure and the installation manner are still relatively complex, and the heat dissipation effect is not good enough.
When the aircraft is fixed on the aircraft, the original elements are synchronous with the aircraft, the dynamic errors generated by vibration, impact and angular motion are reduced, the heat dissipation effect is good, and the temperature drift error can be effectively reduced or eliminated; the simple vibration reduction mounting plate of the inertial navigation system has simpler structure and more convenient installation and use.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides the vibration reduction mounting plate of the inertial navigation system, which has a simple structure and is convenient to use, can keep all elements of an IMU inertial component synchronous with an aircraft when being fixed on the aircraft, reduces dynamic errors generated by vibration, impact and angular motion, keeps the IMU inertial component in a constant temperature state, and reduces temperature drift errors.
The technical scheme is as follows: the utility model provides a be applied to sensitive device's damping mounting panel, the damping mounting panel is integrated into one piece's platelike structure, its cross sectional shape with sensitive device's shape suits and guarantees the focus of damping mounting panel with install in the projection coincidence of sensitive device focus in the bottom on the damping mounting panel, a plurality of mounting holes and spacing stake have been seted up on the damping mounting panel.
Further, the mounting holes are provided in a plurality, and all the mounting holes are symmetrical with respect to the center.
Furthermore, the cross section of the limiting pile is circular, oval or oblong.
Further, the cross section of the vibration reduction mounting plate is rectangular, square, circular or oval.
Further, the damping mounting panel is integrated into one piece's square board, the mounting hole set up in on the four corners and the diagonal of damping mounting panel, spacing stake has two and is the diagonal setting, is the spacing stake of a cross-section for first circular shape spacing stake and cross-section for the second of long circle respectively.
Further, the vibration reduction mounting plate is made of polyformaldehyde plastic, and the polyformaldehyde plastic is homopolymerized formaldehyde.
Furthermore, the vibration reduction mounting plate is formed by injection molding of homo-polyformaldehyde with different properties and then mechanically cutting into a shape which is suitable for the sensitive device.
Further, the sensitive devices comprise a gyroscope and an accelerometer.
The invention has the advantages that:
1) the invention can attenuate high-frequency small-amplitude vibration and is beneficial to heat dissipation of devices, thereby effectively avoiding the influence of temperature change on the IMU;
2) the invention has simple structural design, integrates the functions of installation, fixation, vibration reduction and heat insulation, adopts an external installation mode to synchronously fix all elements of the inertial navigation system and the aircraft, reduces dynamic errors generated by vibration, impact and angular motion, has good heat dissipation effect, reduces temperature drift error, is convenient and quick to install, and simultaneously meets the high standard requirement of the inertial navigation system on vibration reduction and heat insulation;
3) the structure of the invention is integrally formed in the preparation process, is convenient for processing and production, adopts polyformaldehyde as a material with low cost, has safe and simple production process, is suitable for industrial popularization and application, can bear the vibration reduction and heat insulation of devices with higher density and larger weight by adjusting the material proportion and the polymerization degree according to the characteristics of the polyformaldehyde material, and has wide application field.
Drawings
FIG. 1 is a schematic structural view of a damping mounting plate applied to a sensitive device according to embodiment 1 of the present invention;
FIG. 2 shows the shape of the vibration spectrum in Experimental example 1;
shown in the figure: 1. a vibration damping mounting plate; 2. a first limiting pile; 3. a second limiting pile; 4. and (7) installing holes.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without any creative effort belong to the protection scope of the present invention.
It should be noted that the installation methods and technical terms mentioned in the invention are technical terms that are already clearly known in the technical field, and therefore, the explanation is not repeated. Moreover, the same reference numerals are used for the same components, which do not affect and should not constitute an exact understanding of the technical solutions for a person skilled in the art.
Example 1
As shown in fig. 1, the embodiment discloses a vibration damping mounting panel applied to an inertial navigation system, where the vibration damping mounting panel 1 is an integrally formed square plate formed by injection molding polyformaldehyde resin and then mechanically cut into pieces, the vibration damping mounting panel is provided with a plurality of mounting holes 4 and two limiting piles (a first limiting pile 2 and a second limiting pile 3), the mounting holes are respectively disposed at four corners and diagonal lines of the vibration damping mounting panel, the two limiting piles are diagonally disposed, the first limiting pile 2 is a cylindrical limiting pile with a circular cross section, and the second limiting pile 3 is a long circular pile with a long circular cross section (to prevent a sensitive device from generating circular motion and constrained angular motion).
During the specific use, place inertial navigation system on the damping mounting panel in embodiment 1, fix a position through the spacing stake, then pass the mounting hole through the bolt, the another side is fixed with the nut. The inertial navigation system is fixed on the vibration reduction mounting plate in the embodiment 1 of the invention, and then the vibration reduction mounting plate fixed with the inertial navigation system is mounted on a corresponding aircraft.
It should be noted that the plate shape with a square cross section is only an example of the damping mounting plate body 1 of the present invention, and can be made into any shape in practice according to the needs, such as a plate with a rectangular or circular cross section, an oval cross section, and so on. The size of the vibration reduction mounting plate is adjusted according to the actual size of the inertial navigation system, and the thickness of the vibration reduction mounting plate main body 1 can be adjusted to meet the requirements of mounting, vibration reduction and heat insulation in different degrees;
in addition, within the range of acceptable size of the sensitive device, the two limiting piles can be elongated as much as possible when being arranged, so that the error is reduced, and the vibration reduction precision is improved;
polyformaldehyde for manufacturing the vibration reduction mounting plate can also be used for preparing polyformaldehyde resins with different elastic moduli and physical and chemical properties according to different process proportions, and the linear motion of a sensitive device is reduced through the characteristics of the material; the angular motion of the sensitive device is strictly restricted through the arrangement of the mounting holes and the limiting piles.
Experimental example 1 the vibration damping mounting plate of the embodiment 1 is adopted to carry out the functional vibration test of the inertia measurement module
For the vibration test performed on the inertia measurement module (IMU) of type YTDL-M20 applied to a special underwater vehicle after the vibration damping mounting plate of embodiment 1 is mounted, the test method, test conditions, test process and test indexes are as follows:
(1) the test method comprises the following steps: reference standard GJB 150.16A-2009 military equipment laboratory environmental test method part 16: vibration test;
a GJB 7592 and 2012 vibration gyroscope test method;
a GJB 1037A-2004 single-axis pendulum type servo line accelerometer test method;
(2) and (3) testing conditions are as follows: 2.1 test environmental requirements: a) ambient temperature: 15-35 ℃; b) relative humidity: 20% -80%; c) air pressure: atmospheric pressure at the test site.
Site and power supply requirements: a) the foundation of the test bed of the test site is stable, and the test bed is required to meet the standard requirement; b) the test site has good grounding and magnetic environments; c) the IMU is powered using a test board, with a supply voltage of 5V ± 0.02V, unless specified otherwise.
(3) The testing process comprises the following steps: a) after the IMU is provided with the vibration damping device, the IMU and the vibration support are arranged on a vibration table, the X axis is parallel to the vibration direction, a test cable is connected, and the cable is confirmed to be connected correctly;
b) electrifying the IMU, and recording 3min sampling data;
c) starting a vibration table, applying vibration according to the test conditions shown in the figure 2-vibration spectrum shape, and recording 3min sampling data after the vibration table reaches a specified amount;
d) after the vibration is finished, recording the sampling data for 3min, and after the sampling is finished, powering off the IMU;
e) y, Z Axis test was as before.
After the test, the product is subjected to appearance inspection, and whether the fastener is loosened or not and the structure is damaged or not are judged; and in the test process, whether the electrical performance and the mechanical performance of the product are normal or not is checked, and whether the zero-offset change of the gyroscope meets the technical requirements or not during and after the test.
(4) The technical index requirements are as follows: zero-bias variation of the vibrating gyroscope: is better than 2 degrees/h; zero offset change of the accelerometer in vibration: is better than 1 mg;
(5) the test results are shown in table 1 (for the vibration precision calculation method of the gyroscope and the accelerometer, reference is made to the general specification of the GJB 2504-95 quartz flexible accelerometer and the related description in the test method of the GJB 7592 and 2012 vibration gyroscope).
TABLE 1 vibration test results
And (4) conclusion:
and (3) applying vibration to the tested device by using a vibration table according to the vibration spectrum shape shown in the figure 2, testing the zero offset change of the tested device, and sampling data before, during and after vibration for 3min respectively. The results are shown in the table, and the numerical value change of the tested device before and after vibration is far smaller than the error index of vibration precision, which indicates that the applied vibration does not cause functional damage to the precision of the tested device. The mean value of data before and after vibration and the numerical value change in the vibration are in the error range of the vibration precision index, which shows that the external mounting structure plays a certain vibration damping effect in the vibration process, and the functional index of equipment precision is reached.
After the test, the product is subjected to appearance inspection, and no fastener is loosened or the structure is damaged; the electrical performance and the mechanical performance of the product are normal in the test process, and the zero-offset changes of the gyroscope and the accelerometer during and after the test also meet the technical requirements.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof; the present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and any minor modifications, equivalent replacements and improvements made to the above embodiment according to the technical essence of the present invention should be included in the protection scope of the technical solution of the present invention.
Claims (8)
1. A vibration damping device applied to a sensitive device can directly fix the sensitive device on a carrier, and is characterized in that the vibration damping device is a vibration damping mounting plate which is of an integrally formed plate-shaped structure, the cross section of the vibration damping mounting plate is adaptive to the shape of the sensitive device, the center of gravity of the vibration damping mounting plate is ensured to be coincident with the projection of the center of gravity of the sensitive device arranged on the vibration damping mounting plate on the bottom, and the vibration damping mounting plate is provided with a plurality of mounting holes and limiting piles; the vibration reduction mounting plate is made of polyformaldehyde plastic.
2. The vibration damping device applied to the sensitive device according to claim 1, wherein the mounting holes are provided in a plurality, and all the mounting holes are symmetrical about a center.
3. The vibration damping device applied to the sensitive device according to claim 1, wherein the cross section of the limiting pile is circular, oval or oblong.
4. The vibration damping device applied to the sensitive device according to claim 1, wherein the cross section of the vibration damping mounting plate is rectangular, square, circular or oval.
5. The vibration damping device for the sensitive device according to claim 1, wherein the vibration damping mounting plate is an integrally formed square plate, the mounting holes are arranged at four corners and diagonal lines of the vibration damping mounting plate, and the two limiting piles are arranged diagonally and respectively comprise a first limiting pile with a circular cross section and a second limiting pile with an oblong cross section.
6. The vibration damping device applied to the sensitive device according to claim 1, wherein the polyoxymethylene plastic is polyoxymethylene homopolymer.
7. The vibration damping device applied to the sensitive device according to claim 6, wherein the vibration damping mounting plate is formed by injection molding of homo-polyformaldehyde with different properties and then mechanically cut into a shape suitable for the sensitive device.
8. The vibration damping device applied to the sensitive device according to any one of claims 1 to 7, wherein the sensitive device comprises a gyroscope and an accelerometer.
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| CN202210263214.2A CN114353793B (en) | 2022-03-17 | 2022-03-17 | Vibration reduction mounting plate applied to sensitive device |
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Effective date of registration: 20231008 Address after: 5th Floor, Building E, No. 199 Hongwu Avenue, Tangqiao Town, Zhangjiagang City, Suzhou City, Jiangsu Province, 215611 Patentee after: Shijingwei (Zhangjiagang) Information Technology Co.,Ltd. Address before: 300000 101-102, North office building, No. 27, Xingguang Road, Zhongbei Industrial Park, Xiqing District, Tianjin Patentee before: Tianjin spatiotemporal measurement and Control Technology Co.,Ltd. |