CN112182926A - Method for improving vibration reliability of airborne case - Google Patents
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Abstract
The invention provides a method for improving the vibration reliability of an airborne case, which comprises the following steps: the method comprises the following steps: simplifying small parts and small features on the airborne case and establishing a numerical model of the airborne case; step two: determining an external excitation load borne by an airborne case based on an airborne environment working condition; step three: establishing a finite element simulation model of the airborne case; step four: based on a finite element theory, carrying out a numerical simulation test on the airborne case by using finite element software, wherein the numerical simulation test comprises modal analysis and harmonic response analysis of basic excitation, and obtaining modal characteristics and a dynamic response result of the airborne case; step five: according to the dynamic response result, the resonance point of the airborne case is determined to evaluate the vibration stability of the airborne case, whether the stress and amplitude results of the airborne case meet the requirements or not is checked, and the mass distribution and the rigidity distribution of the airborne case can be changed by changing the structural geometry, materials and the like of the airborne case, so that the vibration characteristic of the airborne case is improved, and the vibration reliability of the airborne case is guaranteed.
Description
Technical Field
The invention belongs to the technical field of airborne electronic equipment chassis; in particular to a method for improving the vibration reliability of an airborne machine box.
Background
The airborne electronic equipment case is the foundation of the field work of equipment, and provides a good operating environment capable of resisting the external severe conditions for components and groups in the airborne case. The airborne electronic equipment chassis usually undergoes engineering field work, transportation and installation processes, which make the airborne electronic equipment chassis in a complex loading environment with severe vibration and impact, and these basic vibrations can cause component welding point loosening, open circuit, component damage and the like, and these problems become one of the main causes of system failure at present. With the development of miniaturization and precision of electronic components, the requirements for vibration reliability of the chassis of the airborne electronic equipment are also increased. Therefore, it is very important to improve the vibration reliability of the airborne electronic equipment chassis to ensure the safety of the components in the airborne electronic equipment chassis. Most of the traditional case structures are designed by relying on theoretical calculation and experience, and only the resonance frequency domain of the airborne electronic equipment case product is given, so that the use condition of the airborne electronic equipment case is limited. However, the requirements of modern engineering on products are higher and higher, electronic components are continuously developed in the direction of miniaturization and precision, the application environment is more and more complex, and the traditional method cannot meet the reliability requirements of the chassis of the airborne electronic equipment. In order to overcome the existing problems, the influence of the external environment excitation load characteristic on the airborne electronic equipment chassis needs to be considered in advance, the structure is optimized in the design stage of the airborne chassis, the resonance frequency domain is reduced, and the vibration reliability of the airborne electronic equipment chassis is improved.
Disclosure of Invention
The invention aims to provide a method for improving the vibration reliability of an airborne case.
The invention is realized by the following technical scheme:
the invention relates to a method for improving the vibration reliability of an airborne case, which comprises the following steps:
the method comprises the following steps: simplifying the small characteristics of the case, and establishing a numerical model of the airborne case;
step two: determining an excitation load value of an airborne environment to a chassis;
step three: establishing a finite element model of the airborne case;
step four: performing modal analysis and harmonic response analysis of basic excitation of the airborne case;
step five: determining the resonance point of the airborne case, analyzing the dangerous vibration mode of the structure of the airborne case and the corresponding natural frequency, and evaluating the stability of the airborne case in use, transportation, installation and the like.
Preferably, the method for improving the vibration reliability of the airborne chassis comprises the following specific steps:
the method comprises the following steps: simplifying the small characteristics of the case, and establishing a numerical model of the airborne case;
(1) small features and irrelevant small parts for simplifying case
Neglect the little characteristic such as the little mounting screw hole of the machine carries on quick-witted case to the calculation result influence, simultaneously to the very little components and parts of quality on the machine carries quick-witted case, for example BNC connects, socket, net gape and fan etc. because the quality is very little, do not consider its influence to machine carries quick-witted case structure vibration, simplify it during the modeling.
(2) Building a geometric model
Firstly, establishing a three-dimensional entity model of each simplified part of an airborne case by utilizing SolidWorks software, and then assembling the airborne case to form an assembled body model;
step two: determining an excitation load of an airborne environment on a chassis
And preparing an acceleration load curve of the airborne case according to basic excitation load values and characteristics of various environments encountered by the airborne case in the using, installing and transporting states.
Step three: establishing finite element model of airborne case
(1) Importing airborne case geometric model
Importing the geometric model of the airborne case assembly body established in the step one into finite element analysis software ANSYS according to the file type of the intermediate format;
(2) defining material parameters of airborne chassis structure
The airborne case structure material is made of aluminum alloy, and is regarded as a linear elastic material aiming at the problem of vibration reliability of the airborne case structure, and the density, the elastic modulus, the Poisson ratio and the like of the airborne case structure material are defined
(3) Meshing airborne case structure
The grid division adopts a multi-region grid division method, the grid type is set to be a tetrahedral 10-node secondary unit Solid187, the global grid control is advanced, then the local grid is refined, and the grid transition ratio is set to be 1.3.
(4) Defining boundary conditions and solving settings
Firstly, setting contact, wherein the airborne case is formed by combining a plurality of parts, the contact of each part of the airborne case needs to be defined, and each part of the airborne case is actually fixedly connected, so that the contact is defined as bound connection (bound) in finite element software ANSYS; then, applying a load, and applying a corresponding load to the airborne case according to the load value and the form in the second step; and finally, defining a solving frequency domain.
Step four: performing modal analysis and harmonic response analysis of basic excitation of the airborne case;
and D, performing Modal analysis on the airborne case by using the finite element model of the airborne case established in the step three and a Modal module of finite element analysis software ANSYS to obtain Modal characteristics of the airborne case, including natural frequency, vibration mode and the like, and providing dynamic parameters for the harmonic response analysis of the basic excitation of the airborne case. Meanwhile, the participation coefficient of each order of vibration mode can be obtained, and the main vibration mode is determined; and performing harmonic response analysis on the airborne case by taking the modal analysis as a basis to obtain the amplitude and other dynamic response results of the airborne case when the airborne case is subjected to resonance caused by the excitation frequency of the external working environment and the inherent frequency of the airborne case.
Step five: the method comprises the steps of determining a resonance point of the airborne case, analyzing a dangerous vibration mode and corresponding natural frequency of the structure of the airborne case, evaluating the stability of the airborne case in use, transportation, installation and the like, and optimizing the mass distribution and rigidity distribution of the airborne case by taking corresponding measures, thereby improving the vibration reliability of the structure of the airborne case.
The invention has the following advantages:
(1) the invention provides a method for improving the vibration reliability of an airborne electronic equipment case, which can improve the vibration reliability of the airborne electronic equipment case in a complex use environment.
(2) Under the condition that the influence of external environment excitation load characteristics on the airborne electronic equipment case is considered, modal analysis and fundamental excitation harmonic response analysis are carried out on the airborne electronic equipment case structure in the design stage, the dynamic response result determines the airborne case resonance point, the vibration stability of the airborne case is evaluated, and the mass distribution and the rigidity distribution of the airborne case are changed by changing the structural geometry, materials and the like of the airborne case, so that the vibration characteristics of the airborne case are improved, the vibration reliability of the airborne case is ensured, and certain guiding significance is provided for improving the vibration reliability of the airborne electronic equipment case.
(3) The invention establishes a method for improving the vibration reliability of an airborne electronic equipment case, a finite element simulation calculation model of the airborne electronic equipment case structure is established in finite software ANSYS, modal analysis and fundamental excitation harmonic response analysis are carried out, the modal analysis obtains the natural frequency, the vibration mode and the participation coefficient of each order vibration mode of the airborne electronic equipment case structure, the harmonic response analysis obtains the dynamic response result of the airborne electronic equipment case structure under the excitation of external loads, thereby determining the amplitude and stress results corresponding to the weak area, the resonance frequency domain and the dangerous vibration mode of the airborne electronic equipment case structure, and optimizing the mass distribution and the rigidity distribution of the airborne electronic equipment case based on the analysis result, thereby improving the vibration reliability of the airborne electronic equipment case.
Drawings
FIG. 1 is a graph of the meshing effect of an airborne chassis;
FIG. 2 is a vibration amplitude-frequency characteristic curve of an airborne case;
FIG. 3 is a graph of vibration acceleration change of an airborne enclosure;
fig. 4 is a graph of the vibration stress variation of an airborne chassis.
Detailed Description
The present invention will be described in detail with reference to specific examples. It should be noted that the following examples are only illustrative of the present invention, but the scope of the present invention is not limited to the following examples.
Examples
The embodiment relates to a method for improving the vibration reliability of a chassis of airborne electronic equipment, which comprises the following steps:
the method comprises the following steps: simplifying the small characteristics of the case, and establishing a numerical model of the airborne case;
(1) small features and irrelevant small parts for simplifying case
Neglect the little characteristic such as the little mounting screw hole of the machine carries on quick-witted case to the calculation result influence, simultaneously to the very little components and parts of quality on the machine carries quick-witted case, for example BNC connects, socket, net gape and fan etc. because the quality is very little, do not consider its influence to machine carries quick-witted case structure vibration, simplify it during the modeling. The global analysis is a linear calculation process, local contact nonlinearity is not considered, binding connection of linear behaviors is adopted completely, and relative slippage is limited. Some structural details which have little influence on the whole result are simplified, and the efficiency can be improved.
(2) Building a geometric model
Firstly, establishing a three-dimensional entity model of each simplified part of the airborne case by utilizing SolidWorks software, and then assembling the airborne case to form an assembled body model. And removing irrelevant small parts such as BNC connectors, sockets, net ports, fans and the like on the airborne case, and establishing a simplified three-dimensional geometric model of the airborne case.
Step two: determining an excitation load of an airborne environment on a chassis
According to basic excitation load values and characteristics of various environments encountered by the airborne case in the using, installing and transporting states, an acceleration load curve of the airborne case is prepared, acceleration loading curves in three directions of a space coordinate system need to be made respectively, and the acceleration loading curve is related to continuous dynamic characteristics of the airborne case during harmonic response analysis of basic excitation. Therefore, the excitation load characteristics of various external environments can be fully considered in the design stage of the airborne case, the reliability of the airborne case can be effectively improved, particularly the vibration reliability in a complex and severe vibration impact scene,
step three: establishing finite element model of airborne case
(1) Importing airborne case geometric model
Storing the geometric model of the airborne case assembly body established in the step one into a file type with an intermediate format of an X _ T type, and then importing the file type with the intermediate format into finite element analysis software ANSYS for finite element analysis;
(2) defining material parameters of airborne chassis structure
The airborne case structure material is made of alloy steel and aluminum alloy, and can be regarded as a linear elastic material aiming at the problem of vibration reliability of the airborne case structure, and the density, the elastic modulus, the Poisson ratio and the like of the airborne case structure material are defined. After the material definition is completed, the defined material is endowed to the part of the response of the airborne case, wherein the parameters of the finite element analysis material of the airborne case are shown in the table 1:
TABLE 1
(3) Meshing airborne case structure
The grid division adopts a multi-region grid division method, the grid type is set to be a tetrahedral 10-node secondary unit Solid187, the global grid control is advanced, then the local grid is refined, and the grid transition ratio is set to be 1.3. Each unit node has X, Y, Z translational freedom degrees in 3 directions, and the unit has the characteristics of viscoelasticity, creep stress strengthening, large deformation, large strain and the like. The grid dividing Quality is evaluated by adopting a grid comprehensive Quality evaluation standard (Element Quality), the grid Quality is 0.91, when the grid Quality is 0.85 or more, the grid Quality is better, most of calculations with higher precision requirements can be met, the grid Quality is better, the calculation requirements are met, the number of nodes is 159822, the number of units is 75867, and the grid dividing result is shown in figure 1.
(4) Defining boundary conditions and solving settings
Firstly, contact is set, an airborne case is formed by combining a plurality of parts, the contact is required to be defined for each part of the airborne case, and each part of the airborne case is actually fixedly connected, so that the contact is defined as bound connection (bound) in finite element software ANSYS, the calculation of the contact state of the bound contact type in the software is linear, and the global calculation is ensured to be linear calculation; and then, applying a load, loading an acceleration excitation load on the airborne case according to the load value and the form in the step two, and then defining a modal solving range and a frequency sweeping range of harmonic response analysis of basic excitation.
Step four: performing modal analysis and harmonic response analysis of basic excitation of the airborne case;
carrying out Modal analysis on the airborne case by using the finite element model of the airborne case established in the third step and a Modal module of finite element analysis software ANSYS to obtain Modal characteristics of the airborne case, including natural frequency, vibration mode and the like, counting participation coefficients of each order of vibration mode, determining a main vibration mode of each order, and providing dynamic parameters for harmonic response analysis of basic excitation of the airborne case; the method is characterized in that modal analysis is used as a basis, harmonic response analysis is carried out on an airborne case, when the excitation frequency of the airborne case under the external working environment and the inherent frequency of the airborne case achieve resonance, the amplitude, vibration acceleration, stress and other dynamic response results of the airborne case are obtained, the analysis results can be used for predicting the continuous dynamic characteristics of the structure, whether the structure of the airborne case can resist harmful factors such as resonance, fatigue and other forced vibration or not is verified, whether the structural geometry, materials and the like of the airborne case need to be changed or not, the mass distribution and the rigidity distribution of the airborne case are changed, and therefore the vibration characteristics of the airborne case are improved, and the vibration reliability of the airborne case is guaranteed.
Based on a finite element method and a dynamic modeling theory, the airborne case is equivalent to a discrete system with n smaller elastic units. The influence of damping is not considered, the system is in a free vibration state without exciting load, and a linear dynamic equation of the free vibration of the airborne chassis is established as follows:
in the formula: m is a quality matrix of the structure; k is a stiffness matrix of the structure;
is a unit node acceleration vector; x is a unit node displacement vector; omegaiIs the natural frequency of the system;
is the vibration mode of the system; thetaiIs a phase angle; t is time.
Substituting the formula (2) and the formula (3) into the formula (1) to obtain a characteristic equation:
in discussing the characteristic equation, the equation (4) holds when the following condition is satisfied.
det(K-ωi 2M)＝0 (6)
And (5) representing that the system structure does not vibrate, wherein the free vibration mode of the joint bearing structure in the formula (6) is a characteristic value of an equation, the characteristic value is the square of the natural angular frequency of the system structure, and a characteristic vector corresponding to the characteristic value is the vibration mode of the system structure. The square root of the eigenvalues is ωiThe i-th order free vibration frequency is a natural frequency of the system structure. According to fi＝ωiAnd 2 pi solves the natural frequency fi of the joint bearing system structure. The system has a vibration frequency of fiWhen the mode of vibration is
And obtaining the first 6-order natural frequency value of the airborne case, the vibration mode corresponding to each order of natural frequency and the participation coefficient of each order of vibration mode through modal analysis, and then determining the main vibration mode of the airborne case through the participation coefficient. The modal analysis results are shown in table 2-airborne chassis modal analysis results.
TABLE 2
According to the modal analysis result, the range of the first 6 th order natural frequency of the airborne case is 122Hz to 364Hz, and when the external excitation load frequency is within the range of the natural frequency of the airborne case from 122Hz to 364Hz and the load acting direction is consistent with the vibration mode, the airborne case has high possibility of resonance.
Based on the modal analysis result of the airborne case, the fundamental excitation harmonic response analysis is carried out by using a modal superposition method, the harmonic response sweep frequency range is set to be 50Hz to 350Hz according to the natural frequency result of the airborne case obtained by the modal analysis, the fundamental excitation harmonic response analysis is carried out on the airborne case, and the amplitude-frequency response curve, the vibration acceleration curve, the stress change curve and the like of the airborne case structure under the action of the basic excitation load are obtained through the harmonic response analysis, so that the amplitude, the vibration acceleration, the deformation and the stress of each part of the structure and the like of the airborne case are determined when the external excitation frequency and the natural frequency of the airborne case achieve resonance. The result of the harmonic response analysis is used for predicting the continuous dynamic characteristic of the structure, and whether the system can overcome harmful factors such as resonance, fatigue and other forced vibration is helped to be verified.
As shown in fig. 2, the airborne enclosure resonates strongly at a frequency of about 193Hz, resonates at a frequency of about 303Hz, and has a reduced amplitude. Therefore, when the frequency of the airborne machine box is 193Hz and 303Hz under the excitation effect of the external load, resonance occurs, and the 2 nd order vibration mode and the 4 th order vibration mode of the airborne machine box can be determined to be dangerous vibration modes of the airborne machine box by combining the modal analysis result.
As shown in fig. 3, the acceleration variation curve of the airborne chassis is consistent with the variation trend of the amplitude-frequency characteristic curve, the acceleration has the maximum peak value when the frequency is 193Hz, and the acceleration has the second peak value when the frequency is 303Hz, and the peak values are reduced. When the acceleration of the airborne machine case has a peak value, the airborne machine case can bear great destructive energy in the vibration process, and the airborne machine case and components thereof can be damaged.
As shown in fig. 4, the stress variation curve of the airborne enclosure also shows peaks at 193Hz and 303Hz, the first peak at 193Hz is larger, and the second peak at 303Hz is reduced. When the stress of the airborne machine case has a peak value, the intensity of the airborne machine case is weaker in the vibration process.
Step five: and combining the modal analysis result of the airborne case and the harmonic response analysis result of the basic excitation, determining the natural frequencies of the resonance points of the airborne case to be 193Hz and 303 Hz. The 2 nd order mode shape and the 4 th order mode shape of the airborne machine box are dangerous mode shapes, and the corresponding natural frequencies of the dangerous mode shapes are 193Hz and 303 Hz. When the frequency of the external excitation load is close to 193Hz and 303Hz, the airborne case resonates, and the acceleration and stress change curve has a peak value, which causes the structure of the airborne case to generate larger deformation, violent vibration and the like, causes the airborne case, components and parts in the airborne case, the working performance and the like to break down, and reduces or even destroys the reliability and the safety of the airborne case. According to the mode analysis result and the resonance point, the dangerous vibration mode and the weak structural rigidity position obtained from the fundamental excitation harmonic response analysis result, the structure of the airborne case is optimized, the mass distribution and the rigidity distribution of the airborne case are changed, and the vibration reliability of the airborne case can be improved.
Aiming at the prior art, the invention has the following advantages:
(1) the invention provides a method for improving the vibration reliability of an airborne electronic equipment case, which can improve the vibration reliability of the airborne electronic equipment case in a complex use environment.
(2) Under the condition that the influence of external environment excitation load characteristics on the airborne electronic equipment case is considered, modal analysis and fundamental excitation harmonic response analysis are carried out on the airborne electronic equipment case structure in the design stage, the dynamic response result determines the airborne case resonance point, the vibration stability of the airborne case is evaluated, and the mass distribution and the rigidity distribution of the airborne case are changed by changing the structural geometry, materials and the like of the airborne case, so that the vibration characteristics of the airborne case are improved, the vibration reliability of the airborne case is ensured, and certain guiding significance is provided for improving the vibration reliability of the airborne electronic equipment case.
(3) The invention establishes a method for improving the vibration reliability of an airborne electronic equipment case, a finite element simulation calculation model of the airborne electronic equipment case structure is established in finite software ANSYS, modal analysis and fundamental excitation harmonic response analysis are carried out, the modal analysis obtains the natural frequency, the vibration mode and the participation coefficient of each order vibration mode of the airborne electronic equipment case structure, the harmonic response analysis obtains the dynamic response result of the airborne electronic equipment case structure under the excitation of external loads, thereby determining the amplitude and stress results corresponding to the weak area, the resonance frequency domain and the dangerous vibration mode of the airborne electronic equipment case structure, and optimizing the mass distribution and the rigidity distribution of the airborne electronic equipment case based on the analysis result, thereby improving the vibration reliability of the airborne electronic equipment case.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (6)
1. A method for improving the vibration reliability of an airborne case is characterized by comprising the following steps:
step one, simplifying small characteristics of a case, and establishing a numerical model of an airborne case;
determining an excitation load value of the airborne environment to the chassis;
step three, establishing a finite element model of the airborne case;
fourthly, performing modal analysis of the airborne case and harmonic response analysis of basic excitation;
and fifthly, determining a resonance point of the airborne case, analyzing the dangerous vibration mode of the structure of the airborne case and the corresponding natural frequency, and evaluating the stability of the airborne case in use, transportation and installation.
2. The method for improving the vibration reliability of the airborne chassis according to claim 1, wherein in the first step, the step of transforming the small features of the chassis and establishing the numerical model of the airborne chassis comprises the following specific steps:
(1) small features and irrelevant small parts for simplifying case
Neglecting the installation threaded hole with small influence on the calculation result and components with small mass on the airborne case, and simplifying the components during modeling;
(2) building a geometric model
Firstly, establishing a three-dimensional entity model of each simplified part of the airborne case by utilizing SolidWorks software, and then assembling the airborne case to form an assembled body model.
3. The method for improving the vibration reliability of the airborne cabinet according to claim 1, wherein in the second step, the specific step of determining the value of the excitation load of the airborne environment on the cabinet is as follows: and preparing an acceleration load curve of the airborne case according to basic excitation load values and characteristics of various environments encountered by the airborne case in the using, installing and transporting states.
4. The method according to claim 1, wherein the step three comprises the following specific steps of establishing a finite element model of the airborne chassis:
(1) importing airborne case geometric model
Importing the geometric model of the airborne case assembly body established in the step one into finite element analysis software ANSYS according to the file type of the intermediate format;
(2) defining material parameters of airborne chassis structure
The airborne case structure material is made of aluminum alloy, and is regarded as a linear elastic material aiming at the problem of the vibration reliability of the airborne case structure, and the density, the elastic modulus and the Poisson ratio are defined for the airborne case structure material;
(3) meshing airborne case structure
The grid division adopts a multi-region grid division method, a grid type is set to be a tetrahedral 10-node secondary unit Solid187, advanced global grid control is performed, then local grids are refined, and the grid transition ratio is set to be 1.3;
(4) defining boundary conditions and solving settings
Firstly, setting contact, wherein the airborne case is formed by combining a plurality of parts, the contact of each part of the airborne case needs to be defined, and each part of the airborne case is actually and fixedly connected, so that the contact is defined as binding connection in finite element software ANSYS; then, applying a load, and applying a corresponding load to the airborne case according to the load value and the form in the second step; and finally, defining a solving frequency domain.
5. The method according to claim 1, wherein in step four, the specific steps of performing the modal analysis and the harmonic response analysis of the fundamental excitation of the airborne chassis are as follows:
carrying out Modal analysis on the airborne case by using the finite element model of the airborne case established in the step three and a Modal module of finite element analysis software ANSYS to obtain Modal characteristics of the airborne case and provide dynamic parameters for harmonic response analysis of basic excitation of the airborne case;
and performing harmonic response analysis on the airborne case by taking the modal analysis as a basis to obtain the amplitude and other dynamic response results of the airborne case when the airborne case is subjected to resonance caused by the excitation frequency of the external working environment and the inherent frequency of the airborne case.
6. The method for improving the vibration reliability of the airborne case according to claim 1, wherein in the fifth step, the specific steps of determining the resonance point of the airborne case, analyzing the dangerous vibration mode and the corresponding natural frequency of the structure of the airborne case, and evaluating the stability of the airborne case in use, transportation and installation are as follows: and corresponding measures are taken to optimize the mass distribution and the rigidity distribution of the airborne case, so that the vibration reliability of the airborne case structure is improved.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114096089A (en) * | 2021-11-12 | 2022-02-25 | 复旦大学 | Split type structure of electronic controller and strength simulation method thereof |
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| CN112182926B (en) | 2024-03-22 |
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