CN114169076A - Aviation arc fault damage simulation method based on Fluent software - Google Patents
Aviation arc fault damage simulation method based on Fluent software Download PDFInfo
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Abstract
The invention provides an aviation arc fault damage simulation method based on Fluent software, which is characterized in that a magnetohydrodynamic model is introduced on the basis of a K-epsilon turbulence model of an incompressible flow based on Fluent, and then a relation of plasma physical property parameters changing along with temperature is introduced into a Fluent solver through a user-defined function, so that the simulation calculation of arc in Fluent can be realized. The invention has the beneficial effects that: the electric arc is simulated after the parameters are initialized, the change of the electric characteristics and the temperature field characteristics of the electric arc along with time is obtained, the energy generated after the electric arc occurs can damage surrounding components, and the damage volume of the surrounding components after the electric arc occurs can be extracted through the calculation result.
Description
Technical Field
The invention relates to the technical field of simulation calculation, in particular to an aviation arc fault damage simulation method based on Fluent software.
Background
With the development of multi-electric and all-electric airplanes, an aviation electrical system is more complex, and due to the particularity of airplane environment, poor contact and ablation carbonization of an insulating layer of a wire harness located in a high-temperature and high-vibration area such as an engine compartment and the like can exist; such as in a highly corrosive area such as a drain area, etc., the high insulating performance of the insulation layer of the wire harness is degraded due to long-term salt spray erosion. Under these complex working environments, the probability of an arc fault caused by cable failure is remarkably improved, and the energy generated by the arc fault can cause damage to surrounding components, thereby seriously threatening the flight safety of the airplane. The arc is a discharge phenomenon of gas breakdown, has the characteristics of energy concentration, high temperature and the like, and can rise to 4000K-50000K within a few milliseconds. Furthermore, the narrow space inside the aircraft results in insufficient separation of the cables from the surrounding components, which makes the energy generated by the arc more likely to damage adjacent components. The prevention and damage research of aviation electric arc is becoming the focus of the aviation field.
At present, the arc fault of an airplane is mostly researched from the nature of the arc, and the voltage and current waveforms generated when the arc fault is generated are analyzed so as to distinguish the arc fault from the normal state in a line. The research on the electric arc damage of the airplane is mostly carried out in an experimental mode, but the experiment has the problems of high cost, high difficulty in reproducing an experimental scene and the like.
Disclosure of Invention
In order to solve the problems, the invention aims to provide an aviation arc fault damage simulation method based on Fluent software, which is used for realizing simulation calculation of damage of arc faults to surrounding components. A multi-physical-field coupled aviation arc damage numerical simulation model is constructed by using Fluent software, arc energy data and the damage volume of an aluminum plate are obtained through simulation results, and the simulation results are consistent and have small errors compared with experimental results.
In order to achieve the purpose, the invention adopts the technical scheme that the aviation arc fault damage simulation method based on Fluent software comprises the following steps:
(1) confirming size parameters of an aviation arc occurrence place, comprising the following steps: arc length, cable diameter, aluminum plate thickness, arc to surrounding parts separation distance;
(2) according to the size parameters of the aerial arc occurrence position confirmed in the step (1), constructing a model by using design model software, then performing Meshing on the model by using Meshing software, and outputting a mesh file;
(3) importing the grid file into a Fluent solver, checking the grid quality, and returning to the step (2) if the grid quality is less than 0.8; if the grid mass is greater than 0.8, setting a solver for transient calculation, and setting gravity acceleration, component parameters, material physical property parameters, boundary conditions, a solver model and a solving algorithm;
(4) setting a residual value, initializing the model, setting an ambient temperature and an ambient pressure value when an electric arc occurs, setting a time step length and a calculation step number, and starting calculation;
(5) judging whether the calculation result is converged, if the calculated residual value is lower than the set residual value, judging that the calculation result is converged, if the calculated residual value is converged, finishing the calculation, performing post-processing on the result by utilizing Tecplot post-processing software to obtain the temperature field distribution of the electric arc and the heated temperature field distribution of surrounding components, if the residual value is not converged, adjusting a sub-relaxation factor, returning to the step (4), and recalculating until the residual value is converged;
(6) the volume of damage to surrounding components by the arc was examined.
The solver model in the step (3) comprises a magnetohydrodynamics model, an energy model, a P1 radiation model and a K-epsilon turbulence model.
The temperature rise of the surrounding parts due to the generation of the arc in step (5) is controlled by the heat conduction equation. The heat generated by the arc is transferred to the surrounding components, which increase their temperature, and the damage of the arc to the surrounding components is characterized by the volume of the part whose temperature exceeds its melting point.
The electric arc is a gas discharge phenomenon, and the simulation calculation of the electric arc in the Fluent is realized by introducing an MHD (magnetohydrodynamic model) on the basis of the K-epsilon turbulence model and introducing the relation of the physical property parameters of the plasma along with the temperature change into a Fluent solver through an UDF (user defined function) based on the K-epsilon turbulence model of the incompressible flow of the Fluent. The electric arc is simulated after the parameters are initialized, the change of the electric characteristics and the temperature field characteristics of the electric arc along with time is obtained, the energy generated after the electric arc occurs can damage surrounding components, and the damage volume of the surrounding components after the electric arc occurs can be extracted through the calculation result.
The invention has the following beneficial technical effects:
according to the method, a damage model of the aviation arc fault on the surrounding parts is established by using Fluent software, the temperature field characteristics of the arc fault under different current magnitudes and different initial conditions can be simulated through the model, and the damage condition of the arc on the surrounding parts can be obtained through the temperature field characteristics of the arc through a simulation calculation result. The model can effectively solve the problems of high cost, high difficulty in reproduction of experimental scenes and the like in an experimental method. The damage volume data of the arc fault to surrounding parts can be obtained through the result of the model, and theoretical support is provided for cable layout and device material selection of the airplane.
Drawings
FIG. 1 is a flow chart of model construction according to the present invention;
FIG. 2 is a schematic front view of a model according to an embodiment of the present invention;
FIG. 3 is a schematic side view of a model according to an embodiment of the present invention;
FIG. 4 is an overall temperature profile of an embodiment of the present invention;
FIG. 5 is a graph showing the temperature distribution of an aluminum plate according to an embodiment of the present invention.
Detailed description of the preferred embodiments
The invention is described in further detail below with reference to the following figures and specific examples:
as shown in fig. 1 to 3, the aviation arc fault damage simulation method based on Fluent software of the present invention includes the following steps: (1) the embodiment is a simulation calculation of damage conditions of the aviation arc fault to an aluminum plate structure when the current is 300A. Confirming size parameters of an aviation arc occurrence place, comprising the following steps: the length of the arc, the diameter of the cable, the thickness of the aluminum plate and the spacing distance between the arc and the aluminum plate; temperature and pressure at which arcing occurs. Wherein the arc length is 1mm, the cable diameter is 0.813mm, the aluminum plate thickness is 4mm, and the arc is 0.1mm (considered as no spacing) from the aluminum plate.
(2) And (3) constructing a model by using Designmodeler software according to the size parameters of the aerial arc occurrence position confirmed in the step (1), wherein the length of the model is 26mm, the width of the model is 7mm, and the height of the model is 7 mm. And then, mesh division is carried out on the model by using Meshing software, the aluminum plate and the cable adopt a hexahedral mesh division mode, the air domain adopts a tetrahedral mesh division mode, the number of meshes is 200 ten thousand, the mesh quality is 0.89, and the mesh quality requirement of Fluent is met.
(3) Importing the grid file into a Fluent solver, setting the solver as transient calculation, and setting the gravity acceleration as 9.8m/s2The component parameters comprise an aluminum plate, an air domain and a copper cable, and the physical parameters of the materials comprise density, thermal conductivity, electric conductivity, specific heat capacity and viscosity coefficient, wherein the physical parameters of AL6061 aluminum are shown in Table 1. The boundary condition is set as that the arc current is 300A, a solver model is selected to comprise a magnetohydrodynamics model, an energy model, a P1 radiation model and a K-epsilon turbulence model, and a solution algorithm is selected to be a Couple algorithm.
TABLE 1 physical Properties of AL6061 aluminum
(4) Setting the residual value to be 0.00001, initializing the model, setting the atmospheric temperature when the electric arc occurs to be 300K, setting the air pressure to be 1.325kPa of standard atmospheric pressure, setting the time step length and the calculation step number, and starting to calculate.
(5) And (4) converging residual values, finishing calculation, and performing post-processing on results by utilizing Tecplot post-processing software to obtain the temperature field distribution of the electric arc and the heated temperature field distribution of the aluminum plate.
As shown in fig. 4 and 5, the temperature rise of the aluminum plate due to the arc generation is controlled by the heat conduction equation. The heat generated by the arc transferred to the aluminum plate increased the temperature of the aluminum plate, and the damage to the aluminum plate from the arc was characterized by the volume of the portion of the aluminum plate that exceeded its melting point. In thatIn this example, the current is 300A, and the experimental result of the damaged volume of the aluminum plate is 9.75mm3The simulation result is 10.225mm3The error between the simulation result and the experimental result is acceptable from the viewpoint of aviation safety, so that the reasonability of the arc model and the credibility of the simulation result can be proved.
According to the method, a model of damage of the aviation arc fault to the aluminum plate is established by using Fluent software, the temperature field characteristics of the arc fault under different current magnitudes and different initial conditions can be simulated through the model, and the damage condition of the arc to the aluminum plate can be obtained through simulation calculation according to the temperature field characteristics of the arc. The model can effectively solve the problems of high cost, high difficulty in reproduction of experimental scenes and the like in an experimental method. The damage volume data of the arc to the aluminum plate can be obtained through the result of the model, and theoretical support is provided for the cable layout and the device material selection of the airplane.
It is to be understood that the above description is not intended to limit the present invention, and the present invention is not limited to the above examples, and those skilled in the art may make modifications, alterations, additions or substitutions within the spirit and scope of the present invention.
Claims (4)
1. An aviation arc fault damage simulation method based on Fluent software is characterized by comprising the following steps:
(1) confirming size parameters of an aviation arc occurrence place, comprising the following steps: arc length, cable diameter, aluminum plate thickness, arc to surrounding parts separation distance;
(2) according to the size parameters of the aerial arc occurrence position confirmed in the step (1), constructing a model by using design model software, then performing Meshing on the model by using Meshing software, and outputting a mesh file;
(3) importing the grid file into a Fluent solver, checking the grid quality, and returning to the step (2) if the grid quality is less than 0.8; if the grid mass is greater than 0.8, setting a solver for transient calculation, and setting a gravity acceleration, each component parameter, each material physical property parameter, a boundary condition, a solver model and a solving algorithm;
(4) setting a residual value, initializing the model, setting an ambient temperature and an ambient pressure value when an electric arc occurs, setting a time step length and a calculation step number, and starting calculation;
(5) judging whether the calculation result is converged, if the calculated residual value is lower than the set residual value, judging that the calculation result is converged, if the calculated residual value is converged, finishing the calculation, and performing post-processing on the result by utilizing Tecplot post-processing software to obtain the temperature field distribution of the electric arc and the heated temperature field distribution of surrounding components; if the residual value is not converged, adjusting the sub-relaxation factor, returning to the step (4), and recalculating until the residual value is converged;
(6) the volume of damage to surrounding components by the arc was examined.
2. The aviation arc fault damage simulation method based on Fluent software is characterized in that a solver model in the step (3) comprises a magnetohydrodynamics model, an energy model, a P1 radiation model and a K-epsilon turbulence model,
the formulas (1) and (2) are magnetohydrodynamic models,
in the formulas (1) and (2), sigma is the conductivity,
is the voltage difference, j is the current density, U is the velocity, B0 is the magnetic induction, Q is the Joule heat;
(3) the energy models are shown in the above (4) and (5),
in the formulas (3), (4) and (5), rho is the air plasma density, U is a velocity vector, v is a partial derivative of the volume in the vector in the directions x, y and z, respectively, and g is the gravity acceleration and is 9.8m/s2Mu is air plasma viscosity coefficient, t is time, lambda is air plasma heat conductivity coefficient, htot is specific enthalpy, SM is momentum source term, SE is energy source term,
formula (6) is a P1 radiation model,
in the formula (6), r is a position vector, s' is a stroke length, s is a direction vector, Kav is an absorption coefficient, Ksv is a dispersion coefficient, Iv is a radiation intensity, Ib is a black body emission intensity, v is a frequency, T is a temperature,
for the phase function, Ω is the spatial solid angle and S is the radiation source.
3. The aviation arc fault damage simulation method based on Fluent software is characterized in that in the step (5), the temperature of the peripheral parts is increased due to the generation of the arc, the temperature field distribution of the heating condition of the peripheral parts is controlled by a heat conduction equation, the heat conduction equation is expressed by the formula (7),
in the formula (7), rho is the material density, c is the specific heat capacity of the material, lambda is the thermal conductivity of the material,
is the heat generation rate per unit volume.
4. The aviation arc fault damage simulation method based on Fluent software is characterized in that the damage volume of the inspection arc to surrounding parts in the step (6) is characterized by the volume of a part with the temperature exceeding the melting point.
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| CN202111506493.2A CN114169076A (en) | 2021-12-10 | 2021-12-10 | Aviation arc fault damage simulation method based on Fluent software |
| PCT/CN2022/084559 WO2023103233A1 (en) | 2021-12-10 | 2022-03-31 | Fluent-software-based method for simulating damage of aviation arc fault |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2023103233A1 (en) * | 2021-12-10 | 2023-06-15 | 中国民航大学 | Fluent-software-based method for simulating damage of aviation arc fault |
| CN117216885A (en) * | 2023-11-08 | 2023-12-12 | 中国民航大学 | Aviation direct current grounding arc damage simulation method and system based on COMSOL |
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| CN116629028B (en) * | 2023-07-19 | 2023-09-22 | 东方空间技术(山东)有限公司 | Method and device for determining parameters of flow guide groove of petal-shaped launching pad |
| CN117113777B (en) * | 2023-09-08 | 2024-04-09 | 武汉理工大学 | Drill string vortex-induced vibration calculation method considering internal flow |
| CN118194773A (en) * | 2024-05-16 | 2024-06-14 | 上海交通大学 | Early fault detection method and system for porcelain insulator |
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| US10261120B1 (en) * | 2016-05-27 | 2019-04-16 | National Technology & Engineering Solutions Of Sandia, Llc | Arc plasma-generating systems and methods thereof |
| CN109255170B (en) * | 2018-08-28 | 2022-03-25 | 电子科技大学 | Arc voltage gradient modeling method based on magnetohydrodynamics simulation |
| CN112528527B (en) * | 2021-02-09 | 2021-08-24 | 北京科技大学 | Device and method for simulating and analyzing arc plasma |
| CN114169076A (en) * | 2021-12-10 | 2022-03-11 | 中国民航大学 | Aviation arc fault damage simulation method based on Fluent software |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2023103233A1 (en) * | 2021-12-10 | 2023-06-15 | 中国民航大学 | Fluent-software-based method for simulating damage of aviation arc fault |
| CN117216885A (en) * | 2023-11-08 | 2023-12-12 | 中国民航大学 | Aviation direct current grounding arc damage simulation method and system based on COMSOL |
| CN117216885B (en) * | 2023-11-08 | 2024-02-20 | 中国民航大学 | Aviation direct current grounding arc damage simulation method and system based on COMSOL |
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