CN112182926B - Method for improving vibration reliability of machine-mounted chassis - Google Patents
Method for improving vibration reliability of machine-mounted chassis Download PDFInfo
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Abstract
The invention provides a method for improving vibration reliability of an onboard chassis, which comprises the following steps: step one: small parts and small features on the machine-mounted machine box are simplified, and a numerical model of the machine-mounted machine box is built; step two: determining the external excitation load borne by the airborne chassis based on the airborne environment working condition; step three: establishing a finite element simulation model of the airborne chassis; step four: based on finite element theory, carrying out a numerical simulation test on the airborne chassis by utilizing finite element software, wherein the numerical simulation test comprises modal analysis and harmonic response analysis of basic excitation, and obtaining the modal characteristics and dynamic response results of the airborne chassis; step five: and determining the resonance point of the machine-carried case according to the dynamic response result, evaluating the vibration stability of the machine-carried case, checking whether the stress and the amplitude result of the machine-carried case meet the requirements, and changing the mass distribution and the rigidity distribution of the machine-carried case by changing the structural geometry, the materials and the like of the machine-carried case, thereby improving the vibration characteristics of the machine-carried case and ensuring the vibration reliability of the machine-carried case.
Description
Technical Field
The invention belongs to the technical field of machine cases of airborne electronic equipment; in particular to a method for improving the vibration reliability of an onboard chassis.
Background
The machine case of the airborne electronic equipment is a foundation for the field work of the equipment, and provides a good running environment capable of resisting the external severe conditions for components and groups in the machine case. The onboard electronics chassis is typically subjected to engineering field work, transportation and installation processes, which places the onboard electronics chassis in a complex load environment with severe vibration and impact, and these fundamental vibrations may cause component welding spots to loosen, open circuits, damage to components, etc., so that such problems have become one of the main causes of system failures. Along with the development of miniaturization and precision of electronic components, the requirements for vibration reliability of the machine case of the airborne electronic equipment are also increased. Therefore, it is very important to improve the vibration reliability of the machine case of the airborne electronic equipment to ensure the safety of components in the machine case of the airborne electronic equipment. Most of the traditional chassis structures are designed by relying on theoretical calculation and experience, and only the resonance frequency domain of the chassis products of the onboard electronic equipment is given, so that the use conditions of the chassis of the onboard electronic equipment are 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 reliability requirements of the machine case of the airborne electronic equipment cannot be met by the traditional method. In order to overcome the existing problems, the influence of the excitation load characteristic of the external environment on the machine case of the airborne electronic equipment needs to be considered in advance, the resonance frequency domain is reduced by optimizing the structure in the design stage of the machine case of the airborne electronic equipment, and the vibration reliability of the machine case of the airborne electronic equipment is improved.
Disclosure of Invention
The invention aims to provide a method for improving vibration reliability of an onboard chassis.
The invention is realized by the following technical scheme:
the invention relates to a method for improving vibration reliability of an onboard chassis, which comprises the following steps:
step one: simplifying small characteristics of a case and establishing a numerical model of an airborne case;
step two: determining the excitation load value of the airborne environment to the chassis;
step three: establishing a finite element model of an airborne chassis;
step four: carrying out modal analysis and fundamental excitation harmonic response analysis of the airborne chassis;
step five: and determining resonance points of the machine-mounted machine box, analyzing dangerous vibration modes and corresponding natural frequencies of the machine-mounted machine box structure, and evaluating stability of the machine-mounted machine box in use, transportation, installation and the like.
Preferably, the method for improving the vibration reliability of the onboard chassis comprises the following specific steps:
step one: simplifying small characteristics of a case and establishing a numerical model of an airborne case;
(1) Simplifying small features and irrelevant small parts of a chassis
And small features such as installation threaded holes and the like which have small influence on a calculation result on the airborne chassis are ignored, and meanwhile, for components with small mass on the airborne chassis, such as BNC connectors, sockets, net openings, fans and the like, the influence on the vibration of the airborne chassis structure is not considered due to the small mass, so that the modeling is simplified.
(2) Establishing a geometric model
Firstly, establishing a three-dimensional entity model of each part of the simplified airborne chassis by utilizing SolidWorks software, and then assembling the airborne chassis to form an assembly model;
step two: determining excitation load of airborne environment to chassis
And preparing an acceleration load curve of the airborne chassis according to basic excitation load values and characteristics of various environments encountered by the airborne chassis in use, installation and transportation states.
Step three: finite element model for building airborne chassis
(1) Importing a geometric model of an onboard chassis
Importing the geometrical model of the built machine-mounted chassis assembly body in the step one into finite element analysis software ANSYS in a file type of an intermediate format;
(2) Material parameters defining the structure of an on-board chassis
The machine-mounted chassis structure material adopts aluminum alloy, aiming at the problem of vibration reliability of the machine-mounted chassis structure, the material is regarded as linear elastic material, and density, elastic modulus, poisson ratio and the like are defined for the chassis structure material
(3) Grid-dividing machine-mounted chassis structure
The grid division adopts a multi-region grid division method, the grid type is set to be a tetrahedron 10-node secondary unit Solid187, global grid control is advanced, 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 an onboard chassis is formed by combining parts, the contact needs to be defined for the parts of the onboard chassis, and the parts of the onboard chassis are actually fixedly connected, so that the contact is defined as binding connection (bound) in finite element software ANSYS; then applying load, and applying corresponding load to the airborne chassis according to the load value and the form of the second step; and finally defining and solving a frequency domain.
Step four: carrying out modal analysis and fundamental excitation harmonic response analysis of the airborne chassis;
and (3) carrying out Modal analysis of the airborne chassis by utilizing the finite element model of the airborne chassis established in the step (III) and a Modal module of finite element analysis software ANSYS to obtain Modal characteristics of the airborne chassis, including natural frequency, vibration mode and the like, and providing dynamic parameters for harmonic response analysis of basic excitation of the airborne chassis. Meanwhile, the participation coefficient of each order of vibration mode can be obtained, and the main vibration mode is determined; and carrying out harmonic response analysis on the airborne chassis by taking the modal analysis as a basis to obtain the amplitude and other dynamic response results of the airborne chassis when the excitation frequency of the airborne chassis subjected to the external working environment and the natural frequency of the airborne chassis reach resonance.
Step five: the method comprises the steps of determining resonance points of the machine-mounted machine box, analyzing dangerous vibration modes and corresponding natural frequencies of the machine-mounted machine box structure, evaluating stability of use, transportation, installation and the like of the machine-mounted machine box, and adopting corresponding measures to optimize mass distribution and rigidity distribution of the machine-mounted machine box, so that vibration reliability of the machine-mounted machine box structure is improved.
The invention has the following advantages:
(1) The invention provides a method for improving the vibration reliability of an onboard electronic equipment chassis, which can improve the vibration reliability of the onboard electronic equipment chassis in a complex use environment.
(2) Under the condition that the influence of the external environment excitation load characteristic on the machine case of the airborne electronic equipment is considered, the machine case structure of the airborne electronic equipment is subjected to modal analysis and basic excitation harmonic response analysis in the design stage, the resonance point of the machine case is determined according to the dynamic response result, the vibration stability of the machine case is evaluated, the mass distribution and the rigidity distribution of the machine case are changed by changing the structural geometry, the materials and the like of the machine case, the vibration characteristic of the machine case is improved, the vibration reliability of the machine case is ensured, and certain guiding significance is provided for improving the vibration reliability of the machine case of the airborne electronic equipment.
(3) The invention establishes a method for improving the vibration reliability of an onboard electronic equipment chassis, establishes a finite element simulation calculation model of the onboard electronic equipment chassis structure in finite software ANSYS, carries out modal analysis and harmonic response analysis of basic excitation, obtains the inherent frequency, vibration mode and participation coefficient of each order vibration mode of the onboard electronic equipment chassis structure through modal analysis, obtains the dynamic response result of the onboard electronic equipment chassis structure under external load excitation through harmonic response analysis, and further determines the vibration amplitude and stress result corresponding to the weak area, the resonance frequency domain and the dangerous vibration mode of the onboard electronic equipment chassis structure, optimizes the mass distribution and the rigidity distribution of the onboard electronic equipment chassis based on the analysis result, and improves the vibration reliability of the onboard electronic equipment chassis.
Drawings
FIG. 1 is a meshing effect diagram of an on-board chassis;
FIG. 2 is a graph of vibration amplitude versus frequency characteristics of an on-board chassis;
FIG. 3 is a graph of vibration acceleration change of an on-board chassis;
fig. 4 is a graph of vibration stress variation of an on-board 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 further 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 vibration reliability of a chassis of an onboard electronic device, which comprises the following steps:
step one: simplifying small characteristics of a case and establishing a numerical model of an airborne case;
(1) Simplifying small features and irrelevant small parts of a chassis
And small features such as installation threaded holes and the like which have small influence on a calculation result on the airborne chassis are ignored, and meanwhile, for components with small mass on the airborne chassis, such as BNC connectors, sockets, net openings, fans and the like, the influence on the vibration of the airborne chassis structure is not considered due to the small mass, so that the modeling is simplified. The global analysis is a linear calculation process, local contact nonlinearity is not considered, and binding connection with linear behaviors is adopted completely, so that relative slippage is limited. And the structure details with little influence on the whole result are simplified, and the efficiency can be improved.
(2) Establishing a geometric model
Firstly, a three-dimensional entity model of each simplified part of an airborne chassis is established by utilizing SolidWorks software, and then the airborne chassis is assembled to form an assembly model. And removing irrelevant small parts such as BNC connectors, sockets, net ports, fans and the like on the airborne chassis, and establishing a simplified three-dimensional geometric model of the airborne chassis.
Step two: determining excitation load of airborne environment to chassis
According to basic excitation load values and characteristics of various environments encountered by the airborne chassis in use, installation and transportation states, an acceleration load curve of the airborne chassis is prepared, acceleration loading curves in three directions of a space coordinate system need to be respectively made, and the acceleration loading curves are related to continuous dynamic characteristics of the airborne chassis during harmonic response analysis of basic excitation. In this way, the excitation load characteristics of various external environments can be fully considered in the design stage of the machine-mounted machine box, the reliability of the machine-mounted machine box can be effectively improved, particularly the vibration reliability in complex and severe vibration impact scenes,
step three: finite element model for building airborne chassis
(1) Importing a geometric model of an onboard chassis
The geometrical model of the built machine-mounted chassis assembly body in the first step is stored into an intermediate format file type of an X_T type, and then the intermediate format file type is imported into finite element analysis software ANSYS for finite element analysis;
(2) Material parameters defining the structure of an on-board chassis
The machine-mounted case structure material adopts alloy steel and aluminum alloy, and can be regarded as linear elastic material aiming at the problem of vibration reliability of the machine-mounted case structure, and density, elastic modulus, poisson ratio and the like are defined for the machine-mounted case structure material. After material definition is completed, the defined material is endowed to parts responding to the onboard chassis, wherein the parameters of the finite element analysis material of the onboard chassis are shown in table 1:
TABLE 1
(3) Grid-dividing machine-mounted chassis structure
The grid division adopts a multi-region grid division method, the grid type is set to be a tetrahedron 10-node secondary unit Solid187, global grid control is advanced, then local grids are refined, and the grid transition ratio is set to be 1.3. Each unit node has X, Y, Z translational degrees of freedom in 3 directions, and the unit has the characteristics of viscoelasticity, creep stress reinforcement, large deformation, large strain and the like. Grid division Quality is evaluated by using a grid comprehensive Quality evaluation standard (Element Quality), wherein the grid Quality is 0.91, when the grid Quality is 0.85 or more, the grid Quality is better, the calculation with higher precision requirements for most parts can be met, the grid Quality is better, the calculation requirements are met, the node number is 159822, the unit number is 75867, and the grid division result is shown in fig. 1.
(4) Defining boundary conditions and solving settings
Firstly, setting contact, wherein an onboard chassis is formed by combining parts, the parts of the onboard chassis are required to be defined to be contacted, and the parts of the onboard chassis are actually fixedly connected, so that the contact is defined as binding connection (bound) in finite element software ANSYS, the binding contact type in the software is linear in calculation of the contact state, and the global calculation is ensured to be linear calculation; and then loading the load, loading acceleration excitation load to the airborne chassis according to the load value and form of the second step, and defining a modal solving range and a sweep frequency range for harmonic response analysis of basic excitation.
Step four: carrying out modal analysis and fundamental excitation harmonic response analysis of the airborne chassis;
carrying out Modal analysis of the airborne chassis by utilizing the finite element model of the airborne chassis established in the third step through a Modal module of finite element analysis software ANSYS to obtain Modal characteristics of the airborne chassis, including natural frequency, vibration mode and the like, carrying out statistics on 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 chassis; and carrying out harmonic response analysis on the airborne chassis by taking the modal analysis as a basis to obtain the amplitude, vibration acceleration, stress and other dynamic response results of the airborne chassis when the excitation frequency of the airborne chassis subjected to the external working environment and the natural frequency of the airborne chassis reach resonance, wherein the analysis results can be used for predicting the continuous dynamic characteristics of the structure, verifying whether the structure of the airborne chassis can resist harmful factors such as resonance, fatigue and other forced vibration, and whether the structure geometry, materials and the like of the airborne chassis are required to be changed or not, so as to change the mass distribution and the rigidity distribution of the airborne chassis, thereby improving the vibration characteristics of the airborne chassis and ensuring the vibration reliability of the airborne chassis.
Based on a finite element method and a dynamics modeling theory, the airborne chassis is equivalent to a discrete system with n smaller elastic units. Irrespective of the damping effect, the system is in a free vibration state without excitation load, and a linear dynamics equation of free vibration of the machine-mounted chassis is established as follows:
wherein: m is a mass matrix of the structure; k is the rigidity matrix of the structure;acceleration vectors for the unit nodes; x is a unit node displacement vector; omega i Is the natural frequency of the system; />Is the vibration mode of the system; θ i Is the phase angle; t is time.
Substituting the formula (2) and the formula (3) into the formula (1) to obtain a characteristic equation:
the characteristic equation is discussed, and the equation (4) holds when the following condition is satisfied.
det(K-ω i 2 M)＝0 (6)
The formula (5) shows that the system structure does not vibrate, and the free vibration mode of the knuckle bearing structure in the formula (6) isAnd the characteristic value of the equation is the square of the natural angular frequency of the system structure, and the characteristic vector corresponding to the characteristic value is the vibration mode of the system structure. The square root of the eigenvalue is ω i The i-th order free vibration frequency is the natural frequency of the system structure. According to f i ＝ω i The natural frequency fi of the spherical plain bearing system structure is solved by/2 pi. The vibration frequency of the system is f i When the vibration mode is
And obtaining the first 6-order natural frequency values of the airborne chassis and the vibration modes corresponding to the natural frequencies of each order through modal analysis, and the participation coefficient of each order of vibration modes, and then determining the main vibration mode of the airborne chassis through the participation coefficient. The modal analysis results are shown in table 2-the modal analysis results of the onboard chassis.
TABLE 2
The mode analysis result shows that the front 6-order natural frequency range of the machine case is 122Hz to 364Hz, and when the external excitation load frequency is within the natural frequency range of 122Hz to 364Hz of the machine case and the load acting direction is consistent with the vibration mode, the machine case has high possibility of resonance.
Based on the modal analysis result of the machine case, the harmonic response analysis of basic excitation is carried out by using a modal superposition method, the frequency sweep range of the harmonic response is set to be 50Hz to 350Hz according to the natural frequency result of the machine case obtained by the modal analysis, the harmonic response analysis of the basic excitation is carried out on the machine case, the amplitude-frequency response curve, the vibration acceleration curve, the stress variation curve and the like of the machine case structure under the action of basic excitation load are obtained through the harmonic response analysis, and therefore when the external excitation frequency and the natural frequency of the machine case reach resonance, the amplitude, the vibration acceleration, the deformation and the stress of each part structure and the like of the machine case are determined. The result of the harmonic response analysis is used for predicting the continuous dynamic characteristic of the structure, so as to help verify whether the system can overcome harmful factors such as resonance, fatigue, other forced vibration and the like.
As shown in fig. 2, the on-board chassis resonates sharply at a frequency of about 193Hz and resonates at a frequency of about 303Hz, with a reduction in amplitude. Therefore, resonance can be generated when the frequency of the machine case is 193Hz and 303Hz under the excitation action of external load, and the 2 nd order vibration mode and the 4 th order vibration mode of the machine case can be determined to be dangerous vibration modes of the machine case by combining the modal analysis results.
As shown in fig. 3, the acceleration change curve of the machine case of the machine vehicle is consistent with the change trend of the amplitude-frequency characteristic curve, the acceleration has a maximum peak value when the frequency is 193Hz, and the acceleration has a second peak value when the frequency is 303Hz, so that the peak value is reduced. When the acceleration of the machine-carried case is in a peak value, the machine-carried case can bear great destructive energy in the vibration process, and damage can be caused to the machine-carried case and components thereof.
As shown in fig. 4, the stress variation curve of the on-board chassis also has peaks at frequencies of 193Hz and 303Hz, the peak value of the first peak at 193Hz is larger, and the peak value of the second peak at 303Hz is reduced. When the stress of the on-board chassis peaks, the strength of the machine-mounted case is weaker in the vibration process.
Step five: by combining the modal analysis result of the onboard chassis and the harmonic response analysis result of the basic excitation, the natural frequencies of the resonance points of the onboard chassis can be determined to be 193Hz and 303Hz. The 2 nd order vibration mode and the 4 th order vibration mode of the airborne chassis are dangerous vibration modes, and the natural frequencies corresponding to the dangerous vibration modes are 193Hz and 303Hz. When the frequency of the external excitation load is close to 193Hz and 303Hz, the airborne chassis resonates, the acceleration and stress change curve is at a peak value, which can cause the airborne chassis structure to generate larger deformation, severe vibration and the like, cause the airborne chassis, components and components in the chassis, working performance and the like to generate faults, and reduce or even destroy the reliability and the safety of the airborne chassis. And optimizing the structure of the machine-mounted case according to the resonance points, the dangerous vibration modes and the weak structural rigidity positions obtained by the modal analysis result and the fundamental excitation harmonic response analysis result, changing the mass distribution and the rigidity distribution of the machine-mounted case, and improving the vibration reliability of the machine-mounted case.
The invention has the following advantages in view of the prior art:
(1) The invention provides a method for improving the vibration reliability of an onboard electronic equipment chassis, which can improve the vibration reliability of the onboard electronic equipment chassis in a complex use environment.
(2) Under the condition that the influence of the external environment excitation load characteristic on the machine case of the airborne electronic equipment is considered, the machine case structure of the airborne electronic equipment is subjected to modal analysis and basic excitation harmonic response analysis in the design stage, the resonance point of the machine case is determined according to the dynamic response result, the vibration stability of the machine case is evaluated, the mass distribution and the rigidity distribution of the machine case are changed by changing the structural geometry, the materials and the like of the machine case, the vibration characteristic of the machine case is improved, the vibration reliability of the machine case is ensured, and certain guiding significance is provided for improving the vibration reliability of the machine case of the airborne electronic equipment.
(3) The invention establishes a method for improving the vibration reliability of an onboard electronic equipment chassis, establishes a finite element simulation calculation model of the onboard electronic equipment chassis structure in finite software ANSYS, carries out modal analysis and harmonic response analysis of basic excitation, obtains the inherent frequency, vibration mode and participation coefficient of each order vibration mode of the onboard electronic equipment chassis structure through modal analysis, obtains the dynamic response result of the onboard electronic equipment chassis structure under external load excitation through harmonic response analysis, and further determines the vibration amplitude and stress result corresponding to the weak area, the resonance frequency domain and the dangerous vibration mode of the onboard electronic equipment chassis structure, optimizes the mass distribution and the rigidity distribution of the onboard electronic equipment chassis based on the analysis result, and improves the vibration reliability of the onboard electronic equipment chassis.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the claims without affecting the spirit of the invention.
Claims (1)
1. The method for improving the vibration reliability of the machine-mounted chassis is characterized by comprising the following steps of:
step one, simplifying small characteristics of a case and establishing a numerical model of an airborne case;
step two, determining an excitation load value of the airborne environment to the chassis;
thirdly, establishing a finite element model of the airborne chassis;
fourthly, carrying out modal analysis and harmonic response analysis of basic excitation of the airborne chassis;
fifthly, determining resonance points of the airborne chassis, analyzing dangerous vibration modes of the airborne chassis structure and corresponding natural frequencies, and evaluating the stability of use, transportation and installation of the airborne chassis;
in the first step, the small features of the machine case are converted, and the specific steps for establishing a numerical model of the machine case are as follows:
(1) Simplifying small features and irrelevant small parts of a chassis
Neglecting the installation threaded holes with small influence on the calculation result and components with small mass on the onboard chassis, and simplifying the components during modeling;
(2) Establishing a geometric model
Firstly, establishing a three-dimensional entity model of each part of the simplified airborne chassis by utilizing SolidWorks software, and then assembling the airborne chassis to form an assembly model;
in the second step, the specific steps of determining the excitation load value of the airborne environment to the chassis are as follows: preparing an acceleration load curve of the airborne chassis according to basic excitation load values and characteristics of various environments encountered by the airborne chassis in use, installation and transportation states;
in the third step, the specific steps of building the finite element model of the airborne chassis are as follows:
(1) Importing a geometric model of an onboard chassis
Importing the geometrical model of the built machine-mounted chassis assembly body in the first step into finite element analysis software ANSYS in a file type of an intermediate format;
(2) Material parameters defining the structure of an on-board chassis
The machine-mounted chassis structure material adopts aluminum alloy, aiming at the problem of vibration reliability of the machine-mounted chassis structure, the material is regarded as linear elastic material, and density, elastic modulus and poisson ratio are defined for the chassis structure material;
(3) Grid-dividing machine-mounted chassis structure
The grid division adopts a multi-region grid division method, the grid type is set to be a tetrahedron 10-node secondary unit Solid187, global grid control is advanced, 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 an airborne chassis is formed by combining parts, the contact is required to be defined for the parts of the airborne chassis, and the parts of the airborne chassis are actually fixedly connected, so that the contact is defined as binding connection in finite element software ANSYS; then applying load, and applying corresponding load to the airborne chassis according to the load value and the form of the second step; finally defining and solving a frequency domain;
in the fourth step, the specific steps of performing the modal analysis and the harmonic response analysis of the basic excitation of the airborne chassis are as follows:
carrying out Modal analysis of the airborne chassis by using the finite element model of the airborne chassis established in the third step through a Modal module of finite element analysis software ANSYS to obtain Modal characteristics of the airborne chassis, and providing dynamic parameters for harmonic response analysis of basic excitation of the airborne chassis;
taking the modal analysis as a basis, carrying out harmonic response analysis on the airborne chassis to obtain the amplitude and other dynamic response results of the airborne chassis when the excitation frequency of the airborne chassis subjected to the external working environment and the natural frequency of the airborne chassis reach resonance;
in the fifth step, the resonance point of the airborne chassis is determined, the dangerous vibration mode and the corresponding natural frequency of the airborne chassis structure are analyzed, and the specific steps for evaluating the stability of the use, transportation and installation of the airborne chassis are as follows: and adopting corresponding measures to optimize the mass distribution and the rigidity distribution of the airborne chassis, thereby improving the vibration reliability of the airborne chassis structure.
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