CN114169076A - A simulation method of aviation arc fault damage based on Fluent software - Google Patents

A simulation method of aviation arc fault damage based on Fluent software Download PDF

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CN114169076A
CN114169076A CN202111506493.2A CN202111506493A CN114169076A CN 114169076 A CN114169076 A CN 114169076A CN 202111506493 A CN202111506493 A CN 202111506493A CN 114169076 A CN114169076 A CN 114169076A
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石旭东
刘沛颢
陈业
赵宏旭
张浩天
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Civil Aviation University of China
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Abstract

本发明提供一种基于Fluent软件的航空电弧故障损伤模拟方法，基于Fluent的不可压缩流K‑ε湍流模型，在K‑ε湍流模型的基础上引入磁流体动力学模型，再通过用户自定义函数功能将等离子体物性参数随温度变化关系导入Fluent求解器中，可实现在Fluent中对电弧的模拟计算。本发明的有益效果是：将参数初始化后对电弧进行模拟，得到电弧的电气特性与温度场特性随时间的变化，由于电弧发生后产生的能量会对周围部件造成损伤，通过计算结果可提取电弧发生后周围部件的损伤体积。

Figure 202111506493

The invention provides a simulation method for aviation arc fault damage based on Fluent software. Based on the incompressible flow K-ε turbulence model of Fluent, a magnetohydrodynamic model is introduced on the basis of the K-ε turbulence model, and then a user-defined function is used. The function imports the relationship between plasma physical property parameters and temperature into the Fluent solver, which can realize the simulation calculation of the arc in Fluent. The beneficial effects of the present invention are: after the parameters are initialized, the arc is simulated to obtain the change of the electrical characteristics and temperature field characteristics of the arc with time. Since the energy generated after the arc occurs will cause damage to the surrounding components, the arc can be extracted through the calculation results. Damage volume of surrounding components after occurrence.

Figure 202111506493

Description

Aviation arc fault damage simulation method based on Fluent software
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.
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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
Figure BDA0003404595120000051
(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)

1.一种基于Fluent软件的航空电弧故障损伤模拟方法，其特征在于，包括以下步骤：1. an aviation arc fault damage simulation method based on Fluent software, is characterized in that, comprises the following steps: (1)确认航空电弧发生处的尺寸参数，包括：电弧长度、线缆直径、铝板厚度、电弧与周围部件的间隔距离；(1) Confirm the dimensional parameters of the place where the aviation arc occurs, including: arc length, cable diameter, aluminum plate thickness, and the distance between the arc and surrounding components; (2)根据步骤(1)中确认的航空电弧发生处的尺寸参数，使用Designmodeler软件构建模型，接着使用Meshing软件对模型进行网格划分，并输出网格文件；(2) According to the size parameter of the place where the aviation arc occurs confirmed in step (1), use Designmodeler software to build a model, then use Meshing software to mesh the model, and output the mesh file; (3)将网格文件导入Fluent求解器，检查网格质量，若网格质量小于0.8，则返回步骤(2)；若网格质量大于0.8，则设置求解器为瞬态计算，设置重力加速度、各组分参数、各材料物性参数、边界条件、求解器模型和求解算法；(3) Import the grid file into the Fluent solver and check the grid quality. If the grid quality is less than 0.8, go back to step (2); if the grid quality is greater than 0.8, set the solver to transient calculation and set the acceleration of gravity , each component parameter, each material physical parameter, boundary condition, solver model and solution algorithm; (4)设置残差值，对模型进行初始化，设置电弧发生时的环境温度和环境气压值，设置时间步长与计算步数，开始计算；(4) Set the residual value, initialize the model, set the ambient temperature and ambient pressure value when the arc occurs, set the time step and the number of calculation steps, and start the calculation; (5)判断计算结果是否收敛，若计算残差值低于设定残差值则判定为收敛，若残差值收敛，计算完成，利用Tecplot后处理软件进行结果的后处理，得到电弧的温度场分布，以及周围部件受热的温度场分布；若残差值不收敛，则调节亚松弛因子，返回步骤(4)，重新计算直至残差值收敛；(5) Determine whether the calculation result is converged. If the calculated residual value is lower than the set residual value, it is judged to be converged. If the residual value converges, the calculation is completed, and the Tecplot post-processing software is used to post-process the results to obtain the arc temperature. field distribution, and the temperature field distribution of the surrounding components heated; if the residual value does not converge, adjust the under-relaxation factor, return to step (4), and recalculate until the residual value converges; (6)查看电弧对周围部件的损伤体积。(6) Check the damage volume of the arc to the surrounding parts. 2.根据权利要求1所述的一种基于Fluent软件的航空电弧故障损伤模拟方法，其特征在于，步骤(3)中的求解器模型包括磁流体动力学模型、能量模型、P1辐射模型、K-ε湍流模型，2. a kind of aviation arc fault damage simulation method based on Fluent software according to claim 1, is characterized in that, the solver model in step (3) comprises magnetohydrodynamic model, energy model, P1 radiation model, K -ε turbulence model, 式(1)、(2)为磁流体动力学模型，Equations (1) and (2) are the magnetohydrodynamic model,
Figure FDA0003404595110000021
Figure FDA0003404595110000021
Figure FDA0003404595110000022
Figure FDA0003404595110000022
 式(1)、(2)中，σ为电导率，
Figure FDA0003404595110000023
为电压差，j为电流密度，U为速度，B0为磁感应强度，Q为焦耳热；In formulas (1) and (2), σ is the electrical conductivity,
Figure FDA0003404595110000023
is the voltage difference, j is the current density, U is the speed, B0 is the magnetic induction intensity, and Q is the Joule heat; (3)、(4)、(5)为能量模型，(3), (4), (5) are energy models,
Figure FDA0003404595110000024
Figure FDA0003404595110000024
Figure FDA0003404595110000025
Figure FDA0003404595110000025
Figure FDA0003404595110000026
Figure FDA0003404595110000026
 式(3)、(4)、(5)中，ρ为空气等离子体密度，U为速度矢量，▽为对其中的量在x、y、z方向上分别求偏导，g为重力加速度取9.8m/s2，μ为空气等离子体粘性系数，t为时间，λ为空气等离子体导热系数,htot为比焓,SM为动量源项,SE为能量源项，In formulas (3), (4) and (5), ρ is the air plasma density, U is the velocity vector, ▽ is the partial derivative of the quantities in the x, y, and z directions, respectively, and g is the acceleration of gravity. 9.8m/s 2 , μ is the air plasma viscosity coefficient, t is the time, λ is the air plasma thermal conductivity, htot is the specific enthalpy, SM is the momentum source term, SE is the energy source term, 式(6)为P1辐射模型，Equation (6) is the P1 radiation model,
Figure FDA0003404595110000027
Figure FDA0003404595110000027
 式(6)中，r为位置矢量，s`为行程长度，s为方向矢量，Kav为吸收系数，Ksv为散色系数，Iv为辐射强度，Ib为黑体发射强度，v为频率，T为温度，
Figure FDA0003404595110000028
为相位函数，Ω为空间立体角，S为辐射源。In formula (6), r is the position vector, s` is the stroke length, s is the direction vector, Kav is the absorption coefficient, Ksv is the dispersion coefficient, Iv is the radiation intensity, Ib is the black body emission intensity, v is the frequency, T is temperature,
Figure FDA0003404595110000028
is the phase function, Ω is the solid angle of space, and S is the radiation source. 3.根据权利要求1所述的一种基于Fluent软件的航空电弧故障损伤模拟方法，其特征在于，步骤(5)中周围部件由于电弧产生而导致的温度上升，周围部件受热情况的温度场分布由热传导方程控制，热传导方程如式(7)，3. a kind of aviation arc fault damage simulation method based on Fluent software according to claim 1, is characterized in that, in step (5), the temperature rise of surrounding parts due to arc generation, the temperature field distribution of surrounding parts heating situation Controlled by the heat conduction equation, the heat conduction equation is as in Eq. (7),
Figure FDA0003404595110000031
Figure FDA0003404595110000031
 式(7)中，ρ为材料密度，c为材料比热容，λ为材料导热系数，
Figure FDA0003404595110000032
为单位体积的发热率。In formula (7), ρ is the material density, c is the material specific heat capacity, λ is the material thermal conductivity,
Figure FDA0003404595110000032
is the heating rate per unit volume. 4.根据权利要求1所述的一种基于Fluent软件的航空电弧故障损伤模拟方法，其特征在于，步骤(6)所述查看电弧对周围部件的损伤体积是由温度超过熔点部分的体积表征。4. a kind of aviation arc fault damage simulation method based on Fluent software according to claim 1, is characterized in that, described in step (6), the damage volume of arc to surrounding parts is characterized by the volume of the temperature exceeding the melting point part.
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Cited By (5)

* Cited by examiner, † Cited by third party
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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
CN119066893A (en) * 2024-11-06 2024-12-03 合肥航太电物理技术有限公司 A method for simulating damage of aviation arc fault
CN119066893B (en) * 2024-11-06 2025-01-17 合肥航太电物理技术有限公司 Aviation arc fault damage simulation method

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