CN115525964A - Fiber reinforced composite material lattice sandwich structure damping optimization and design method - Google Patents

Fiber reinforced composite material lattice sandwich structure damping optimization and design method Download PDF

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CN115525964A
CN115525964A CN202210954974.8A CN202210954974A CN115525964A CN 115525964 A CN115525964 A CN 115525964A CN 202210954974 A CN202210954974 A CN 202210954974A CN 115525964 A CN115525964 A CN 115525964A
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damping
cae
geometric model
sandwich structure
composite material
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洪毅
司丙麒
赫晓东
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Harbin Institute of Technology
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Abstract

A damping optimization and design method for a fiber reinforced composite dot matrix sandwich structure belongs to the technical field of vibration and noise reduction of composite dot matrix sandwich structures. The method solves the problems of low accuracy of theoretical prediction of the damping performance of the composite material dot matrix sandwich structure and poor optimization effect of the geometric parameters based on the damping performance. According to the invention, the stress and strain components of each unit of the composite material lattice sandwich structure are obtained through modal analysis, and the modal damping of the structure is solved by combining a modal strain energy method, so that a set of method for accurately forecasting the damping performance of the composite material lattice sandwich structure is provided, the structure can be optimally designed based on the damping forecasting result, the optimization effect is improved, and a basis is provided for the design of the fiber reinforced composite material lattice sandwich structure with the vibration reduction requirement. The method can be applied to the technical field of vibration and noise reduction of the composite material lattice sandwich structure.

Description

Fiber reinforced composite material lattice sandwich structure damping optimization and design method
Technical Field
The invention belongs to the technical field of vibration and noise reduction of composite material dot matrix sandwich structures, and particularly relates to a damping optimization and design method of a fiber reinforced composite material dot matrix sandwich structure.
Background
In recent years, ships with high efficiency and large propelling speed are rapidly developed, and phenomena of main structure vibration and noise of the ships are increasingly prominent. Under the influence of vibration and noise, part of the working performance of the ship is influenced, such as poor concealment, shortened service time of the ship caused by fatigue phenomena and the like. For this reason, it is necessary to try to reduce the hull vibrations to counteract these adverse effects.
The composite material has the advantages of high specific strength, high specific stiffness, good damping performance, good designability, good corrosion resistance and the like, and is widely applied to the fields of aerospace, ship construction and the like. The sandwich structure of composite material is a new type light structure, and is formed from upper and lower face plates and intermediate core layer, and the face plates are small in thickness, large in rigidity, and the core layer is large in thickness and light in weight. The sandwich structure can be divided into different types such as a dot matrix sandwich structure, a honeycomb sandwich structure, a folded sandwich structure and the like according to different topological structures of the sandwich layer. Researches show that the composite material dot matrix sandwich structure has more excellent performance in the aspects of light weight and low-frequency dynamic response, a batch of achievements for researching the damping performance of the composite material laminated plate are available at home and abroad at present, but the researches on the damping performance of the composite material dot matrix sandwich structure and the optimization of geometric parameters based on the damping performance are less, the theoretical prediction accuracy of the damping performance of the composite material dot matrix sandwich structure is lower, and the optimization effect of the geometric parameters based on the damping performance is poorer. Therefore, it is very important to provide an effective, convenient and high-accuracy prediction method for the damping performance of the composite material lattice sandwich structure and perform optimal design.
Disclosure of Invention
The invention aims to solve the problems of low accuracy of theoretical prediction of damping performance of a composite material dot matrix sandwich structure and poor optimization effect of geometric parameters based on the damping performance, and provides a damping optimization and design method of a fiber reinforced composite material dot matrix sandwich structure.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a damping optimization and design method for a fiber reinforced composite material lattice sandwich structure specifically comprises the following steps:
step one, establishing a CAE geometric model of a fiber reinforced composite dot matrix sandwich structure by using 3D modeling software, and introducing the established CAE geometric model into Workbench;
step two, setting material parameters of the fiber reinforced composite material in Workbench, and then setting a layering condition and a boundary condition;
carrying out modal analysis after the CAE geometric model is subjected to meshing to obtain stress and strain components of each unit;
step three, solving modal damping of the CAE geometric model based on the stress and strain components obtained in the step two;
step four, selecting any parameter of the CAE geometric model as a variable parameter, fixing other parameters of the CAE geometric model, continuously adjusting the value of the variable parameter, repeating the step one to the step three to obtain modal damping corresponding to each value of the variable parameter, performing curve fitting on the value of the variable parameter and the obtained modal damping, and taking the value of the variable parameter corresponding to the damping extreme value in the curve fitting result as the optimal value of the selected variable parameter;
step five, sequentially selecting each parameter of the CAE geometric model as a variable parameter, and repeating the process of the step four for each variable parameter to respectively obtain the optimal value corresponding to each parameter of the CAE geometric model;
and step six, establishing an optimized CAE geometric model according to the optimal value corresponding to each parameter of the CAE geometric model, and solving modal damping of the optimized CAE geometric model to complete damping optimization.
Further, the 3D modeling software utilized for establishing the CAE geometric model of the fiber reinforced composite material lattice sandwich structure is SolidWorks.
In the second step, the material parameters of the fiber reinforced composite material are set in an orthopic Elasticity module of Workbench, and the material parameters of the core rod are set in an isotpic Elasticity module of Workbench.
Further, the specific process of the third step is as follows:
Figure BDA0003790900380000021
Figure BDA0003790900380000022
Figure BDA0003790900380000023
where K denotes the cell number, K =1,2, …, N, N denotes the total number of cells, p is the component number, p =1,2, …,6,
Figure BDA0003790900380000024
representing the pth stress component of the kth cell,
Figure BDA0003790900380000025
representing the p-th strain component, V, of the Kth cell K The volume of the K-th cell is shown,
Figure BDA0003790900380000026
denotes the p-th material specific damping capacity component of the K-th cell and ψ denotes the modal damping.
Further, the parameters of the CAE geometric model include a core rod section form, a core rod inclination angle, a panel ply number and a panel ply angle.
The beneficial effects of the invention are:
according to the invention, the stress and strain components of each unit of the composite material lattice sandwich structure are obtained through modal analysis, and the modal damping of the structure is solved by combining a modal strain energy method, so that a set of method for accurately forecasting the damping performance of the composite material lattice sandwich structure is provided, the structure can be optimally designed based on the damping forecasting result, the optimization effect is improved, and a basis is provided for the design of the fiber reinforced composite material lattice sandwich structure with the vibration reduction requirement.
Drawings
FIG. 1 is a flow chart of calculation of stress, strain component and damping of a fiber reinforced composite material lattice sandwich structure;
FIG. 2 is a schematic diagram of a lattice sandwich structure geometric model drawn based on SolidWorks in the embodiment;
FIG. 3 is a diagram illustrating modal analysis results obtained based on Workbench in an embodiment;
FIG. 4 is a diagram of the damping calculation results obtained based on APDL command streams in an embodiment;
FIG. 5 is a plot of ply angle versus damping fit for one example.
Detailed Description
First embodiment this embodiment will be described with reference to fig. 1. The damping optimization and design method for the lattice sandwich structure of the fiber reinforced composite material comprises the following steps:
step one, establishing a CAE geometric model of a fiber reinforced composite material lattice sandwich structure by using 3D modeling software, and importing the established CAE geometric model into Workbench;
step two, setting material parameters (referring to material mechanical property parameters) of the fiber reinforced composite material in Workbench, and then setting a layering condition and a boundary condition;
carrying out modal analysis after meshing the CAE geometric model to obtain stress and strain components of each unit;
thirdly, solving modal damping of the CAE geometric model based on the stress and strain components obtained in the second step;
step four, selecting any parameter of the CAE geometric model as a variable parameter, fixing other parameters of the CAE geometric model, continuously adjusting the value of the variable parameter, repeating the step one to the step three to obtain modal damping corresponding to each value of the variable parameter, performing curve fitting on the value of the variable parameter and the obtained modal damping, and taking the value of the variable parameter corresponding to the damping extreme value in the curve fitting result as the optimal value of the selected variable parameter;
in the step, the first-order modal damping, the second-order modal damping, the third-order modal damping and the fourth-order modal damping corresponding to each value of the variable parameter are directly obtained, and curve fitting is performed on the value of the variable parameter and the obtained fourth-order modal damping;
step five, sequentially selecting each parameter of the CAE geometric model as a variable parameter, and repeating the process of the step four for each variable parameter to respectively obtain the optimal value corresponding to each parameter of the CAE geometric model;
and step six, establishing an optimized CAE geometric model according to the optimal value corresponding to each parameter of the CAE geometric model, and solving modal damping of the optimized CAE geometric model to complete damping optimization.
And designing the fiber reinforced composite material lattice sandwich structure according to the optimal value corresponding to each parameter of the CAE geometric model, namely realizing the optimal design of the fiber reinforced composite material lattice sandwich structure.
The second embodiment is as follows: the difference between the embodiment and the specific embodiment is that the 3D modeling software used for establishing the CAE geometric model of the fiber reinforced composite lattice sandwich structure is SolidWorks.
Other steps and parameters are the same as those in the first embodiment.
The third concrete implementation mode: the second embodiment is different from the first or second embodiment in that, in the second step, the material parameters of the fiber reinforced composite material are set in the Workbench, the panel material parameters are set in the orthogonal Elasticity module of the Workbench, and the core rod material parameters are set in the Isotropic Elasticity module of the Workbench.
Other steps and parameters are the same as those in the first or second embodiment.
The fourth concrete implementation mode: the difference between this embodiment and one of the first to third embodiments is that the specific process of the third step is:
Figure BDA0003790900380000041
Figure BDA0003790900380000042
Figure BDA0003790900380000043
where K denotes the cell number, K =1,2, …, N, N denotes the total number of cells, p is the component number, p =1,2, …,6,
Figure BDA0003790900380000044
representing the pth stress component of the kth cell,
Figure BDA0003790900380000045
representing the p-th strain component, V, of the Kth cell K The volume of the K-th cell is shown,
Figure BDA0003790900380000046
representing the p-th material specific damping capacity component of the K-th cell,
Figure BDA0003790900380000047
as material parameters need to be specified in advance, ψ denotes modal damping.
The modal damping of each order is calculated by the method of the embodiment, and the definition of p =1,2, …,6, pp in the embodiment refers to: when p =1, only consider
Figure BDA0003790900380000048
Component, when p =2, only consider
Figure BDA0003790900380000049
Component, when p =3, only consider
Figure BDA00037909003800000410
Component, when p =4, only consider
Figure BDA00037909003800000411
Component, when p =5, only consider
Figure BDA00037909003800000412
Component(s) ofWhen p =6, only consider
Figure BDA00037909003800000413
Components, and no other components are considered.
Other steps and parameters are the same as those in one of the first to third embodiments.
The fifth concrete implementation mode: different from the first embodiment to the fourth embodiment, the parameters of the CAE geometric model include a cross-sectional form of the core rod, an inclination angle of the core rod, a number of panel layers, and a panel layer angle.
And adjusting the section form of the core rod piece, the inclination angle of the core rod piece and the number of the panel layers, redrawing a geometric model in SolidWorks, and setting and adjusting the panel layer angles in a modal analysis module in Workbernch.
Other steps and parameters are the same as in one of the first to fourth embodiments.
Examples
In the embodiment, a certain type of carbon fiber composite panel and a certain type of aluminum alloy material are adopted for damping calculation and optimal design, and the method specifically comprises the following steps:
the method comprises the following steps: a lattice sandwich structure geometric model is established in SolidWorks, as shown in figure 2, the length of the geometric model is 130mm, the width of the geometric model is 10mm, the total thickness of the geometric model is 6mm, the unit cell form of a core layer is Kagome type, the side length of the unit cell is 5mm, the section of a rod piece is a square with the side length of 1mm, and the inclination angle of the rod piece is 40.6 degrees.
Step two: setting material parameters, wherein the panel material in the embodiment is a carbon fiber composite material of a certain type, is regarded as an Orthotropic material, and is set by using an Orthotropic Elasticity module; the core rod piece is made of certain aluminum alloy materials, is regarded as Isotropic materials, and is arranged by using Isotropic Elasticity modules.
Entering a Modal Modal analysis module, realizing the panel layering effect by utilizing a local coordinate system, and setting the panel layering effect as [0 degree/90 degree/0 degree ]. And (5) grid division is carried out, so that the grid division is ensured to be fine enough, and otherwise, the damping calculation result is not converged. And finally, setting a boundary condition that one end is fixedly supported and the other end is free, and solving. The obtained results of the modal analysis are shown in fig. 3.
Step three: adding APDL command stream in the Solution part, writing a modal damping extraction program, running the Solution again, calculating modal damping of each order, and recording the calculation result of the damping as shown in FIG. 4.
Step four: in the embodiment, the panel layering is taken as a variable, the middle panel layering angle is sequentially adjusted to be 75 degrees, 60 degrees, 45 degrees, 30 degrees, 15 degrees and 0 degrees, the steps are repeated, and the modal damping is recorded.
Step five: the intermediate ply angle is used as a variable, the obtained data is used for making a ply angle-damping fitting curve, as shown in fig. 5, and the extreme value is obtained by using the modal damping of a certain order as an optimization index.
Step six: and optimizing all the geometric parameters to finally obtain the maximum damping value.
In the embodiment, for the case of a given length, width and thickness, the panel layer adopts [45 °/-45 °/45 ° ], the inclination angle of the rod is about 50 °, the sectional area of the rod is increased within the allowable range of condition constraint, better damping performance can be obtained, and the optimal value of the specific damping capacity of the embodiment can reach 8.47%.
The above-described calculation examples of the present invention are merely to explain the calculation model and the calculation flow of the present invention in detail, and are not intended to limit the embodiments of the present invention. It will be apparent to those skilled in the art that other variations and modifications of the present invention can be made based on the above description, and it is not intended to be exhaustive or to limit the invention to the precise form disclosed, and all such modifications and variations are possible and contemplated as falling within the scope of the invention.

Claims (5)

1. The damping optimization and design method of the fiber reinforced composite material lattice sandwich structure is characterized by comprising the following steps of:
step one, establishing a CAE geometric model of a fiber reinforced composite dot matrix sandwich structure by using 3D modeling software, and introducing the established CAE geometric model into Workbench;
step two, setting material parameters of the fiber reinforced composite material in Workbench, and then setting a layering condition and a boundary condition;
carrying out modal analysis after the CAE geometric model is subjected to meshing to obtain stress and strain components of each unit;
thirdly, solving modal damping of the CAE geometric model based on the stress and strain components obtained in the second step;
step four, selecting any parameter of the CAE geometric model as a variable parameter, fixing other parameters of the CAE geometric model, continuously adjusting the value of the variable parameter, repeating the step one to the step three to obtain modal damping corresponding to each value of the variable parameter, performing curve fitting on the value of the variable parameter and the obtained modal damping, and taking the value of the variable parameter corresponding to the damping extreme value in the curve fitting result as the optimal value of the selected variable parameter;
step five, sequentially selecting each parameter of the CAE geometric model as a variable parameter, and repeating the process of the step four for each variable parameter to respectively obtain the optimal value corresponding to each parameter of the CAE geometric model;
and step six, establishing an optimized CAE geometric model according to the optimal value corresponding to each parameter of the CAE geometric model, and solving modal damping of the optimized CAE geometric model to complete damping optimization.
2. The method for optimizing and designing the damping of the fiber reinforced composite lattice sandwich structure according to claim 1, wherein the 3D modeling software used for establishing the CAE geometric model of the fiber reinforced composite lattice sandwich structure is SolidWorks.
3. The method for optimizing and designing damping of the lattice sandwich structure of the fiber reinforced composite material according to claim 2, wherein in the second step, material parameters of the fiber reinforced composite material are set in Workbench, namely, panel material parameters are set in an Orthopic Elasticity module of Workbench, and core rod material parameters are set in an Isotropic Elasticity module of Workbench.
4. The damping optimization and design method for the lattice sandwich structure of the fiber reinforced composite material according to claim 3, wherein the concrete process of the third step is as follows:
Figure FDA0003790900370000011
Figure FDA0003790900370000012
Figure FDA0003790900370000021
where K denotes the cell number, K =1,2, …, N, N denotes the total number of cells, p is the component number, p =1,2, …,6,
Figure FDA0003790900370000022
representing the pth stress component of the kth cell,
Figure FDA0003790900370000023
denotes the p-th strain component, V, of the Kth element K The volume of the K-th cell is shown,
Figure FDA0003790900370000024
denotes the p-th material specific damping capacity component of the K-th cell and ψ denotes the modal damping.
5. The method for optimizing and designing damping of the lattice sandwich structure of the fiber reinforced composite material according to claim 4, wherein the parameters of the CAE geometric model include a section form of a core rod, an inclination angle of the core rod, the number of the panel layers and a layer angle of the panel layers.
CN202210954974.8A 2022-08-10 2022-08-10 Fiber reinforced composite material lattice sandwich structure damping optimization and design method Pending CN115525964A (en)

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