CN109446702B - Passive vibration reduction method of space science experiment cabinet - Google Patents
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- CN109446702B CN109446702B CN201811331112.XA CN201811331112A CN109446702B CN 109446702 B CN109446702 B CN 109446702B CN 201811331112 A CN201811331112 A CN 201811331112A CN 109446702 B CN109446702 B CN 109446702B
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Abstract
The invention relates to a passive vibration damping method of a space science experiment cabinet, which comprises the steps of establishing a finite element simulation model of the space science experiment cabinet in front and rear processing software, and carrying out sine frequency sweep analysis and solving to obtain acceleration response results of the whole body and all components; obtaining the energy distribution of the whole cabinet and each component on a resonance frequency point; laying a constraint damping layer at a position where the modal strain energy of the key component is larger; and (3) performing sine frequency sweep analysis and solving again on the space science experiment cabinet after the damping vibration attenuation is laid, and comparing the change conditions of the front and rear structure responses of the additional constrained damping layer to verify the reliability of the passive vibration attenuation method. The invention provides a passive vibration reduction method for a space science experiment cabinet, which does not need to change the existing structure, has no influence on the structure function of a cabinet body, improves the dynamic environment of instrument equipment and effective load to a certain extent, improves the comprehensive performance index of the experiment cabinet, and has high reliability, strong robustness and easy realization.
Description
Technical Field
The invention relates to the field of aerospace constrained damping vibration attenuation design, in particular to a passive vibration attenuation method for a space science experiment cabinet.
Background
Vibration is a mechanical problem often encountered in the development of aerospace system structures, and if the vibration is not properly handled, the vibration environment of the structure is too severe, or a resonance phenomenon occurs, so that instrument failure or even catastrophic results can be caused. Therefore, structural vibration damping technology is a very critical factor for the development of aerospace system products.
In the second phase of manned spaceflight, china will develop a space laboratory which is attended by people in a short time, and a series of space science experiments will be developed. In order to construct a laboratory, the carrier rocket can bear a plurality of space scientific experimental cabinets to perfect the space laboratory and meet the requirements of scientific experiments. The space science experiment cabinet is used for bearing a scientific load system, is provided with a plurality of high-precision instruments and equipment to assemble a space laboratory and completes a space science experiment. The requirements of the high-precision instruments and equipment on the vibration environment are high, the precision of the high-precision instruments and equipment can be affected due to irreversible damage to the high-precision instruments and equipment under the working condition of high vibration dynamics, space scientific experiments cannot be carried out after the last day, and huge loss is generated, so that the requirements of special scientific experiments can be met only by adopting necessary vibration reduction measures, and the research and design are carried out on the passive vibration reduction system of the space scientific experiment cabinet.
Disclosure of Invention
Aiming at the problem of large response of precision mechanical vibration in severe aerospace dynamic environment, the invention provides a passive vibration attenuation method of a space science experiment cabinet, which adopts a constrained damping layer vibration attenuation technology to improve the damping of the experiment cabinet, improve the dynamic environment and further improve the reliability of the space science experiment cabinet in a rocket launching state.
And correcting the finite element model by using a small amount of data obtained by the structural test to obtain a more accurate finite element model, so that the problem of inaccurate finite element modeling simulation is solved.
The technical scheme adopted by the invention for realizing the purpose is as follows:
a passive vibration reduction method for a space science experiment cabinet comprises the following steps:
step 1: establishing a finite element simulation model of the space science experiment cabinet in front and rear processing software, and performing sine frequency sweep analysis and solving through finite element analysis software to obtain acceleration response results of the whole and each component;
step 2: obtaining energy distribution of the whole cabinet and each component on a resonance frequency point by adopting a modal strain energy analysis method;
and 3, step 3: paving damping materials including damping layers and constraint layers at positions with larger modal strain energy of the key components;
and 4, step 4: and (3) carrying out sine frequency sweep analysis solving on the space science experiment cabinet after the damping vibration attenuation is laid again, and verifying the reliability of the passive vibration attenuation method by comparing the change conditions of the front and rear structure responses of the additional constrained damping layer.
The sine frequency sweep analysis solving is to carry out frequency response analysis on the XYZ directions of the experiment cabinet respectively to obtain the acceleration response results of the whole body and each component, determine the frequency of the maximum vibration and the acceleration response amplification condition of the existing experiment cabinet, and also lay a cushion for comparing the acceleration response results obtained by carrying out frequency response analysis on the follow-up structure and the vibration-damped structure.
The modal strain energy analysis method is characterized in that modal analysis is carried out on an original structure to obtain energy distribution of the whole cabinet and each component on a resonance frequency point, and the bonding position of the constrained damping layer is determined according to the modal strain energy distribution.
The damping material is a factor of priority consideration of the design of a constrained damping structure, and is required to have a high loss factor at the vibration reduction frequency, wherein the damping layer is made of butyl rubber.
The damping layer and the constraint layer are laid on a vibration-damped structure with large strain energy in a finite element model, and the damping layer and the constraint layer are suitable for a sheet plane structure. Therefore, the base layer is generally a shell grid, the damping layer is simulated by a pentahedron or hexahedron unit, the constraint layer is simulated by a shell grid unit, and the base layer, the damping layer and the constraint layer are coupled into a whole through a common node.
The passive vibration damping method mainly uses a damping vibration damping technology, and utilizes the deformation of a damping material under the action of alternating stress to convert kinetic energy into heat so as to achieve the aim of vibration damping. The constraint damping layer structure is formed by bonding a constraint layer and a viscoelastic damping layer and is attached to the surface of the damped structure (base layer) in a bonding mode. When the structure vibrates, the damping layer is sheared and deformed, and the energy dissipation capacity of the structure is enhanced.
The invention has the following beneficial effects and advantages:
the invention can be further popularized and applied to the aspect of vibration reduction and noise reduction design of key sections of an aerospace system, has the characteristics of small modification on the structure by adopting an additional constrained damping layer vibration reduction scheme, high reliability and low realization cost, can improve the dynamic environment of instrument equipment and effective load to a certain extent, and improves the comprehensive performance index and reliability of products.
Drawings
FIG. 1 is a flow chart of a method of the present invention;
FIG. 2 is a structural diagram of a space science laboratory cabinet;
FIG. 3 is a cloud of skin assembly modal strain energy distributions;
FIG. 4 is a schematic view of a main body of a skin laying down a restraint damping layer;
FIG. 5 is a constrained damping layer finite element model; wherein 1 is a restraint layer, 2 is a damping layer and 3 is a skin substrate.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples.
Fig. 1 shows a flow chart of the method of the present invention.
The process of the passive vibration damping method for the space science experiment cabinet mainly comprises the following four steps:
establishing a finite element simulation model of the space science experiment cabinet in the preprocessing software Hypermesh, simplifying the whole structure into a solid body, a shell and a concentrated quality unit, adopting an RBE2 rigid unit to simulate bolt connection, and carrying out modal frequency response analysis and solution in XYZ three directions through MSC. The pre-processing software and the post-processing software and the finite element simulation analysis software comprise: hyperWorks, MSC. Patran & Nastran, ANSYS, ABAQUS, LMSVirual. Lab.
And secondly, in order to carry out vibration reduction on the experiment cabinet by sticking the viscoelastic constraint damping layer, the spreading of the damping layer has pertinence, and the spreading position of the damping layer is arranged in a strain energy distribution area corresponding to a main vibration mode with large vibration response, so that the vibration reduction effect is most remarkable. And adopting a modal strain energy analysis method, solving and obtaining the energy distribution of the whole cabinet and each component on a resonance frequency point through Lanuss modal analysis, and further determining the laying position of the constrained damping layer.
Paving damping materials at positions with larger modal strain energy of the key components, wherein the damping materials comprise a damping layer and a constraint layer, the damping layer is simulated by a pentahedral or hexahedral unit, the constraint layer is simulated by a shell grid unit, and the damping layer, the pentahedral or hexahedral unit, the constraint layer and the shell grid unit are coupled into a whole through common nodes; the damping material is a factor which is preferably considered in the design of a constrained damping structure, and is required to have a high loss factor at the vibration reduction frequency, wherein the damping layer is made of butyl rubber.
And fourthly, carrying out modal frequency response analysis and solving in the XYZ three directions again on the space science experiment cabinet after the damping vibration attenuation is laid, obtaining acceleration response results of the whole and all components, comparing change conditions of front and rear structure responses of the additional constrained damping layer, and verifying the reliability of the passive vibration attenuation method.
Example (b):
the invention aims at a certain space science experiment cabinet and adopts passive vibration attenuation of a constrained damping layer.
Fig. 2 is a structural composition diagram of a space science experiment cabinet.
The space science experiment cabinet mainly comprises a cabinet body metal frame structure and an internal scientific load, and the outside of the whole metal frame is surrounded by a skin.
Firstly, establishing a finite element simulation model of a space science experiment cabinet in a front and back processing software Hypermesh, simplifying the whole structure into a solid, a shell and a concentrated mass unit, adopting an RBE2 rigid unit to simulate bolt connection, and respectively carrying out sinusoidal response analysis (the global damping ratio is 0.05) on three XYZ directions of the experiment cabinet through MSC.Nastran to respectively obtain acceleration response cloud pictures of the whole and each component and a response curve of a specific measuring point on a concerned backboard. This analysis is on the one hand in order to confirm the acceleration response amplification condition of current laboratory cabinet under the sinusoidal frequency sweep operating mode, and on the other hand is intended to be compared with the model of follow-up additional restraint damping layer.
Sine sweep frequency analysis through the scientific experiment cabinet discovers that the acceleration response of the whole experiment cabinet is overlarge, and the concrete expression is as follows: the back plate and the scientific load module mounted on the back plate are particularly prominent. By taking the response of a measuring point of the back plate as an investigation focus and analyzing and solving modal frequency response, the maximum response of the main structure back plate of the scientific experiment cabinet in three directions is as follows: 14.8g (73 Hz) in the X direction, 5.9g (59 Hz) in the Y direction, and 28.7g (94 Hz) in the Z direction. According to the frequency response analysis result, the backboard has the maximum response in the Z direction, and the resonant peak frequency is 94Hz.
As the main structure of the experiment cabinet is manufactured, in order to change as little as possible and achieve the effect of vibration control on the premise of meeting the mass constraint, a viscoelastic constraint damping layer method is selected for vibration reduction. It is common in aerospace (especially in satellite applications), and it does not require modification of existing structures. The constraint damping layer structure is formed by bonding a constraint layer and a viscoelastic damping layer and is attached to the surface of the damped structure (base layer) in a bonding mode. The damping vibration attenuation technology is that when the structure vibrates, a damping layer generates shear deformation, the energy dissipation capacity of the structure is enhanced, kinetic energy is converted into heat, and the purpose of vibration attenuation is achieved. The dynamic performance of the viscoelastic material is related to the magnitude of the strain borne by the structure, and the larger the strain, the larger the deformation of the damping material, and the more energy is consumed. In order to determine the optimal pasting position of the constrained damping layer, modal analysis is carried out on the original structure, and strain distribution of the structure under the resonance frequency is checked.
In order to reduce vibration of the experiment cabinet by sticking the viscoelastic constraint damping layer, the spreading of the damping layer is targeted, and because the back plate has the largest response to acceleration in the Z direction, the spreading position of the damping layer is arranged in the corresponding strain energy distribution area under the Z-direction main vibration mode, so the vibration reduction effect is most obvious. And adopting a modal strain energy analysis method, solving and obtaining the energy distribution of the whole cabinet and each component on a resonance frequency point through Lanuss modal analysis, and further determining the laying position of the constrained damping layer.
The vibration reduction technology of the constrained damping layer is suitable for being applied to the surface of a plane structure of a thin plate, and the largest thin plate structure of the space science experiment cabinet is a skin assembly wrapping the whole cabinet body, so that the skin is selected as a base layer for the space science experiment cabinet, and the constrained damping layer is applied on the skin. And finding the modal strain energy distribution condition of the skin assembly under the resonance frequency of 94Hz of the Z-direction main vibration mode by a Lanussian modal analysis method. As shown in FIG. 3, the modal analysis result shows that most of the strain energy at the Z-direction resonance frequency of 94Hz is distributed on the partial surface of the skin, and the strain energy is not distributed basically at the four windows of the skin and the rear cover. Therefore, the scheme only applies a constraint damping layer at the strain energy distribution position of the skin main body, as shown in figure 4.
The constrained damping vibration reduction design needs to determine the bonding position of the constrained damping layer and also needs to determine the material and thickness parameters of the damping layer and the constrained layer. The damping material is a factor which is preferably considered in the design of a constrained damping structure, and the material is required to have a high loss factor at the vibration reduction frequency, wherein the damping layer is made of butyl rubber, and the constrained layer is made of a structural member material which is adhered to a base layer, namely the skin material. The constraining layer and damping layer material properties are shown in table 1.
TABLE 1 constraint layer and damping layer Material Properties
And laying a constraint damping layer at a position with larger skin modal strain energy, wherein the constraint damping layer comprises a damping layer and a constraint layer. The covering base layer is a shell grid, the damping layer is simulated by a pentahedron or hexahedron unit, the constraint layer is simulated by a shell grid unit, and the three are coupled into a whole through a common node, as shown in figure 5.
And (3) carrying out sinusoidal frequency sweep analysis and solution in three directions of XYZ again on the space science experiment cabinet after the damping vibration attenuation is laid, obtaining an acceleration response result of the back plate assembly, and comparing the change conditions of the front and rear structure responses of the additional constrained damping layer, as shown in Table 2.
TABLE 2 comparison of Z-Direction response results
It can be seen from the above table that the Z-direction back plate acceleration response is reduced to 22.8g from 28.7g of the original model after the constrained damping layer is laid for vibration reduction, the vibration response is reduced by about 21%, and the vibration reduction effect is obvious by adopting the constrained damping layer passive vibration reduction scheme aiming at the space science experimental cabinet.
The discovery introduces a passive vibration reduction method of a space science experiment cabinet, the maximum position of modal strain energy and an energy transfer path are obtained by a Lanuss modal extraction method, the bonding position of a constrained damping layer is determined according to the magnitude of the modal strain energy, and the energy dissipation capacity of a structure is enhanced by utilizing the damping material to bear larger shear deformation and part of tension and compression deformation under the action of alternating stress, so that the damping effect of the whole structure is increased to achieve the purpose of vibration reduction. The passive constraint damping layer vibration attenuation method is high in reliability and strong in robustness, and can effectively reduce the amplitude of a vibration response resonance peak value under the condition that the rigidity and the quality of a system are not obviously changed. The scheme can be further popularized and applied to the design aspect of damping and noise reduction of key parts of an aerospace system, the dynamic environment of instruments and equipment and effective loads can be improved to a certain extent, and the comprehensive performance index and the reliability of products are improved.
Claims (6)
1. A passive vibration reduction method of a space science experiment cabinet is characterized in that: the method comprises the following steps:
step 1: establishing a finite element simulation model of the space science experiment cabinet in front and rear processing software, and performing sine frequency sweep analysis and solving through finite element analysis software to obtain acceleration response results of the whole cabinet and each component;
and 2, step: obtaining energy distribution of the whole cabinet and each component on a resonance frequency point by adopting a modal strain energy analysis method;
and 3, step 3: paving a constrained damping layer at a position with larger modal strain energy according to energy distribution;
establishing a constrained damping layer model on a paved component of a finite element model of a space science experiment cabinet, carrying out sine frequency sweep analysis and solution on the space science experiment cabinet paved with the constrained damping layer to obtain an acceleration response result of the whole cabinet and each component, comparing the acceleration response result with the acceleration response result of the whole cabinet and each component before the constrained damping layer is paved, and ending the paving process if the acceleration response result is reduced by more than 10%; otherwise, selecting the damping material with the grade different from that of the current damping material, and paving again.
2. The passive vibration damping method of the space science experimental cabinet according to claim 1, characterized in that: the restraint damping layer includes damping layer and restraint layer, and wherein, damping layer and the laminating of being laid the subassembly.
3. The passive vibration damping method of the space science experimental cabinet according to claim 2, characterized in that: the damping material of the damping layer is butyl rubber.
4. The passive vibration damping method of the space science experimental cabinet according to claim 2, characterized in that: the constraint layer material is the same as the material of the laid component.
5. The passive vibration damping method of the space science experimental cabinet according to claim 1, characterized in that: the paved component is of a thin plate plane structure.
6. The passive vibration damping method of the space science experimental cabinet according to claim 1, characterized in that: the constrained damping layer model comprises:
the damping layer is simulated by a pentahedral or hexahedral unit, and the constraint layer is simulated by a shell grid unit and is coupled with the paved component model into a whole through a common node.
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| CN110562501A (en) * | 2019-09-27 | 2019-12-13 | 中国科学院沈阳自动化研究所 | Space station is with compound damping scientific experiment cabinet that attenuates vibration |
| CN111473985A (en) * | 2020-05-12 | 2020-07-31 | 中国科学院沈阳自动化研究所 | Thermal analysis test bed of composite damping vibration attenuation scientific experiment cabinet |
| CN113591200B (en) * | 2021-06-07 | 2023-05-12 | 北京临近空间飞行器***工程研究所 | Friction clearance fit strut connecting structure dynamic characteristic analysis method |
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| US6298963B1 (en) * | 1999-02-25 | 2001-10-09 | The United States Of America As Represented By The Secretary Of The Navy | Tuned broadband vibrational dissipator |
| CN107368645A (en) * | 2017-07-17 | 2017-11-21 | 华东交通大学 | A kind of restriction damping layer structural vibration computational methods |
| CN108652286A (en) * | 2018-04-24 | 2018-10-16 | 航天材料及工艺研究所 | A kind of space station scientific experimentation cabinet skin assemblies and preparation method |
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| US6298963B1 (en) * | 1999-02-25 | 2001-10-09 | The United States Of America As Represented By The Secretary Of The Navy | Tuned broadband vibrational dissipator |
| CN107368645A (en) * | 2017-07-17 | 2017-11-21 | 华东交通大学 | A kind of restriction damping layer structural vibration computational methods |
| CN108652286A (en) * | 2018-04-24 | 2018-10-16 | 航天材料及工艺研究所 | A kind of space station scientific experimentation cabinet skin assemblies and preparation method |
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