CN112528540B - Structure optimization method based on force-heat coupling calculation - Google Patents
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Abstract
The application belongs to the field of optimization of structural parameters of aircrafts, and particularly relates to a structural optimization method based on force-heat coupling calculation. The method comprises the following steps: the method comprises the following steps of firstly, obtaining design variables to be optimized, constraint conditions and an optimization target; secondly, establishing a geometric model according to the design variables, and establishing a finite element model according to the geometric model; calculating a first temperature field at an initial moment according to the finite element model, and obtaining a first stress field after thermal stress deformation according to the first temperature field at the initial moment; constructing an optimus calculation model, and calculating a second temperature field and a force-heat coupling second stress field at each moment in the full-profile range; and fifthly, constructing an optimus optimization model, loading the second temperature field and the second stress field into the optimus optimization model, and calculating the optimal solution of the design variables. According to the method and the device, a large amount of human resources can be saved, the precision of the optimal design is increased, and the efficiency of the optimal design is improved.
Description
Technical Field
The application belongs to the field of optimization of structural parameters of aircrafts, and particularly relates to a structural optimization method based on force-heat coupling calculation.
Background
The transient temperature field calculation at a certain moment can be realized through commercial finite element software such as ansys, abaqus and the like, the transient temperature field calculation at each moment on the full flight envelope needs to be realized according to the temperature field calculation result at the previous moment, the result is used as the interpolation basis for heat flow density load input to redistribute the heat flow density input load, and meanwhile, the temperature field result at the previous moment is used as the preload for the transient temperature field calculation at the next moment, so the transient temperature field calculation in the full envelope range needs to be completed by finite element secondary development programming.
At present, a mature technology for calculating a full-flight envelope transient temperature field does not exist, and an automatic flow and a program for performing full-flight envelope force thermal coupling calculation by taking a structural temperature field and static load as input do not exist. In addition, in the prior art, most of the structure optimization technologies are based on static calculation and dynamic calculation, parameters such as stress, deformation and weight are taken as constraint conditions, the lightest weight, the minimum stress and the minimum deformation are taken as optimization targets, the structure optimization design of factors such as temperature, thermal expansion and thermal stress on the full flight envelope curve is not considered, and an automatic flow platform capable of achieving the transient temperature calculation, the thermal stress calculation and the structure optimization calculation of the full flight envelope curve is not available. In addition, optimization based on full flight envelope requires a large number of finite element calculations, and the current existing optimization techniques are not sufficient to support a large number of temperature and force thermal coupling calculations.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The present application aims to provide a structural optimization method based on force-thermal coupling calculation, so as to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
a structural optimization method based on force thermal coupling calculation comprises the following steps:
the method comprises the following steps of firstly, obtaining design variables, constraint conditions and optimization targets to be optimized;
secondly, establishing a geometric model according to the design variables, and establishing a finite element model according to the geometric model;
calculating a first temperature field at an initial moment according to the finite element model, and obtaining a first stress field after thermal stress deformation according to the first temperature field at the initial moment;
constructing an optimus calculation model, and calculating a second temperature field and a force-heat coupling second stress field at each moment in the full-profile range;
and fifthly, constructing an optimus optimization model, loading the second temperature field and the second stress field into the optimus optimization model, and calculating the optimal solution of the design variables.
Optionally, in the first step, the design variables include: aircraft skin thickness, air inlet duct wallboard thickness, spray pipe inner wall thickness, support frame web thickness, wing rib web thickness.
Optionally, in the first step, the constraint conditions include deformation, stress, and a maximum temperature of the model within a preset range, and the optimization target is the lightest weight.
Optionally, in the second step, the establishing a geometric model according to the design variables, and the establishing a finite element model according to the geometric model includes:
establishing a geometric model according to the design variables;
and carrying out mesh division on the geometric model, wherein the thin-wall structure uses shell units, the beam structure uses beam units, and corresponding material attributes are configured for each part to obtain a finite element model.
Optionally, the material properties include density, modulus of elasticity, specific heat capacity, coefficient of thermal expansion, and material plasticity parameters.
Optionally, in step three, the calculating a first temperature field at an initial time according to the finite element model includes:
s301, obtaining the heat flow density load of the finite element model;
s302, setting an initial moment, loading the heat flow density load of the initial moment onto the finite element model, and performing transient temperature calculation in a finite element abaqus to obtain a first temperature field of the initial moment of the finite element model.
Optionally, in the third step, the obtaining the first stress field after the thermal stress deformation according to the first temperature field at the initial time includes:
s303, taking the first temperature field as a calculated predefined field;
s304, setting an initial moment, loading the aerodynamic force load of the initial moment on the finite element model, and carrying out force thermal coupling calculation in the finite element abaqus to obtain a first stress field of the initial moment of the finite element model.
Optionally, in step four, constructing an optimus calculation model, and calculating a second temperature field and a second stress field of the force-thermal coupling at each time within the full-profile range includes:
s401, constructing a first optimus calculation model, and calculating a second temperature field of each moment in a full-profile range, wherein the temperature field obtained by calculation at the last moment is used as a predefined field of the current calculation moment;
s402, constructing a second optimus calculation model, and calculating a force-thermal coupling second stress field at each moment in the full-profile range, wherein the temperature field obtained by calculation at the current moment is used as a predefined field for force-thermal coupling calculation at the current moment.
The invention has at least the following beneficial technical effects:
according to the structure optimization method based on force-heat coupling calculation, the integrated full-automatic optimization platform integrating the transient temperature calculation, the force-heat coupling calculation and the structure optimization calculation of the full-flight envelope is considered, the structural transient temperature field calculation in the flight full-envelope range is carried out, then the force-heat coupling calculation is carried out by superposing aerodynamic force, the optimization efficiency can be improved, the manual operation error is reduced, the load working condition is considered comprehensively, and therefore the high-precision optimization design of the aircraft structure is achieved.
Drawings
FIG. 1 is a flow chart of a method for structural optimization based on force-thermal coupling calculation according to an embodiment of the present application;
FIG. 2 is a schematic diagram of the heat flow density loading of a structural optimization method based on force-thermal coupling calculation according to an embodiment of the present application;
FIG. 3 is a schematic diagram of aerodynamic loading of a structural optimization method based on force-thermal coupling calculation according to an embodiment of the present application;
FIG. 4 is a schematic diagram of an optimal time calculation model of a structural optimization method based on force-thermal coupling calculation according to an embodiment of the present application;
FIG. 5 is a schematic diagram of an optimus optimization model of a structural optimization method based on force-thermal coupling calculation according to an embodiment of the present application;
FIG. 6 is a schematic diagram illustrating the optimization results of a structural optimization method based on force-thermal coupling calculation according to an embodiment of the present application;
fig. 7 is a schematic diagram of a constraint-compliant optimization result of a structural optimization method based on force-thermal coupling calculation according to an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 5.
The application provides a structure optimization method based on force-heat coupling calculation, which is characterized by comprising the following steps of:
the method comprises the following steps of firstly, obtaining design variables to be optimized, constraint conditions and an optimization target;
step two, establishing a geometric model according to the design variables, and establishing a finite element model according to the geometric model;
calculating a first temperature field at the initial moment according to the finite element model, and obtaining a first stress field after thermal stress deformation according to the first temperature field at the initial moment;
constructing an optimus calculation model, and calculating a second temperature field and a force-heat coupling second stress field at each moment in the full-profile range;
and fifthly, constructing an optimus optimization model, loading the second temperature field and the second stress field into the optimus optimization model, and calculating the optimal solution of the design variable.
According to the structural optimization method based on force-heat coupling calculation, in the first step, design variables needing optimization, such as thickness of aircraft skin, thickness of an air inlet channel wall plate, thickness of an inner wall surface of a spray pipe, thickness of a supporting frame web plate, thickness of a wing rib web plate and other thin-wall structures and area of a beam section, are selected; the constraint conditions are that the deformation, the stress and the highest temperature of the model are in a design range, and the optimization target is the lightest weight.
The mathematical model of the optimization problem in this application is expressed as:
Min Mass
σ<σ0，ξ<ξ0，T<T0
{t 1 、t 2 、t 3 ……，s 1 、s 2 、s 3 ……}
in the formula, Mass is the total Mass of the model, sigma, xi and T are respectively the maximum stress, maximum deformation and maximum temperature of the model, sigma 0, xi 0 and T0 are corresponding constraint values, and T 1 、t 2 、t 3 ……，s 1 、s 2 、s 3 … … is a set of variations in thin wall thickness and beam cross-sectional area.
In the structural optimization method based on force-heat coupling calculation, in the second step, establishing a geometric model according to the design variables, and establishing a finite element model according to the geometric model includes:
establishing a geometric model according to the design variables;
and carrying out mesh division on the geometric model, wherein the thin-wall structure uses shell units, the beam structure uses beam units, and corresponding material attributes are configured for each part to obtain a finite element model.
According to the method, the aircraft geometric model is established in three-dimensional modeling software, the geometric model is led into meshing software for meshing, the shell unit is used in the thin-wall structure, the beam unit is used in the beam structure, and corresponding material attributes are given to all parts. The material properties need to be changed according to the temperature, including density, elastic modulus, specific heat capacity and thermal expansion coefficient, and plastic parameters need to be given in consideration of plastic deformation. When the composite material laminated plate is selected, equivalent calculation needs to be carried out on the material properties of the composite material laminated plate, and the material properties are given according to the corresponding anisotropic materials.
In the third step, a first temperature field packet at the initial time is calculated according to a finite element model, and obtaining a first stress field after thermal stress deformation according to the first temperature field at the initial time includes:
s301, obtaining the heat flow density load of the finite element model;
s302, setting an initial moment, loading a heat flow density load at the initial moment on a finite element model, and performing transient temperature calculation in a finite element abaqus to obtain a first temperature field at the initial moment of the finite element model;
s303, taking the first temperature field as a calculated predefined field;
s304, setting an initial moment, loading the aerodynamic force load of the initial moment on the finite element model, and carrying out force thermal coupling calculation in the finite element abaqus to obtain a first stress field of the initial moment of the finite element model.
In the calculation of the transient temperature field at the initial moment, the heat flux density load of the model is obtained, and the load is in the form of a time history hot wall heat flux curve changing along with Mach number and flight altitude; selecting an initial moment, loading the heat flow density load of the initial moment on the finite element model, simultaneously giving the initial temperature of the model of 20 ℃ and proper radiation parameters for balancing, and performing transient temperature calculation in a finite element abaqus so as to obtain the temperature distribution of the initial moment of the finite element model.
In the fourth step, an optimus calculation model is constructed, and calculating a second temperature field at each moment in the full-profile range and a second stress field of the force-heat coupling includes:
s401, constructing a first optimus calculation model, and calculating a second temperature field of each moment in a full-profile range, wherein the temperature field obtained by calculation at the last moment is used as a predefined field of the current calculation moment;
the heat flux density of the current calculation time node is obtained through Mach number-wall surface temperature two-dimensional linear interpolation, wherein the wall surface temperature is the temperature of the previous time node, and an interpolation program is written through a python program. The heat flow density equation is as follows:
q＝h*(T0-T1)
wherein q is the heat flow density, h is the convective heat transfer coefficient, T0 is the total incoming flow temperature, T1 is the wall temperature, h and T0 are fixed values in the heat flow calculation process, and the wall temperature T1 is a finite element node temperature value at a certain moment, so that it can be seen that the heat flow and the node temperature are in a linear relationship, and therefore the method for obtaining the heat flow input by linear interpolation is feasible.
S402, constructing a second optimus calculation model, and calculating a force-thermal coupling second stress field at each moment in the full-profile range, wherein the temperature field obtained by calculation at the current moment is used as a predefined field for force-thermal coupling calculation at the current moment. And (3) atmospheric pressure load of a node at the current calculation time, obtaining the pressure load corresponding to the Mach number at the current time through linear interpolation, and completing full-profile force thermal coupling automatic calculation in a second optimal calculation model.
According to the structure optimization method based on force-heat coupling calculation, an optimus optimization model is constructed, and optimization integration is achieved in optimus. Firstly, analyzing an input and output file, wherein the file analysis is a key link for building an optimization platform, the input file analysis tells optimus to design variables, and the design variable thickness value combination is updated by setting an optimus optimization algorithm; and selecting the serious working condition of the thermal stress calculation on the full flight profile in the last step as an optimization input file. The output file analyzes and tells optimus the data to be extracted, the constraint value and the objective function value, namely the maximum stress, the maximum strain, the maximum temperature value and the model weight. And running an optimization flow and result analysis, reasonably selecting an optimization strategy provided by options, and performing sample point selection and automatic optimization calculation by software according to the upper and lower variable limits, the single variable quantity and the optimization strategy selected by a user. And obtaining a final calculation result, and obtaining an optimal solution through an optimus post-processing function.
In one embodiment of the present application, the design variables to be optimized are first selected: thickness t of wall plate in different areas of aircraft 1 、t 2 、t 3 、t 4 (ii) a The constraint conditions include that the deformation and the stress of the wall plate and the highest temperature of the model are in a design range, and the optimization goal is the lightest weight.
The mathematical model of the optimization problem in this application is expressed as:
Min Mass
σ<σ0，ξ<ξ0，T<T0
wherein Mass is total Mass of the model, sigma, xi and T are maximum stress, maximum deformation and maximum temperature of the model, sigma 0, xi 0 and T0 are corresponding constraint values, and variable T 1 、t 2 、t 3 、t 4 The variation range is 1 to 10 with an interval of 0.5.
Secondly, establishing a geometric model and a finite element model: establishing an aircraft geometric model in three-dimensional modeling software, importing the geometric model into meshing software for meshing, using a shell unit for a thin-wall structure, endowing each part with corresponding material properties, and giving out material plasticity parameters according to temperature changes including density, elastic modulus, specific heat capacity and thermal expansion coefficient and considering plastic deformation.
Then, the transient first temperature field calculation at the initial moment is carried out, and the method comprises the following steps: (a) and (3) obtaining heat flow loads of the outer wall surface and the inner flow channel of the aircraft, wherein the load form is a time-history hot wall heat flow curve changing along with Mach number and flight altitude, as shown in fig. 2, the first three rows are node coordinates in a load calculation model, the fourth row and the fifth row are heat flow density values when the wall surface temperature of the flight altitude 1 with the Mach number of 0.1 is 100 and 200 ℃, the sixth row and the seventh row are heat flow density values when the wall surface temperature of the flight altitude 2 with the Mach number of 0.5 is 100 and 200 ℃, and the rest is done until the flight section is finished. The aerodynamic load is a time history curve changing with mach number and flight altitude, as shown in fig. 3, the first three columns are node coordinates in the load calculation model, the fourth column is an atmospheric pressure value when the mach number is 0.1 and the flight altitude is 1, and the rest is repeated until the flight section is finished. (b) Taking the flight altitude 1 with the Mach number of 0.1 as an initial time, loading the heat flow density load of the initial time on a finite element model, simultaneously giving the initial temperature of the model of 20 ℃ and balancing proper radiation parameters, and performing transient temperature calculation in a finite element abaqus to obtain the initial time temperature distribution of the finite element model, wherein the files are heat0.cae and heat0.odb.
Obtaining a first stress field after thermal stress deformation according to the distribution of the first temperature field at the initial moment: and taking the initial temperature field as a predefined field for calculation, applying an initial moment aerodynamic load, and performing force thermal coupling calculation in a finite element abaqus to obtain initial moment stress distribution of a finite element model, wherein the documents are expand0.cae and expand0.odb.
Further, an optimus calculation model is built, and a temperature field and a force-thermal coupling stress field at each moment in the full-section range are calculated: (a) taking the temperature field obtained by calculation at the previous moment as a predefined field of the current calculation moment; (b) the heat flux density of the current calculation time node is obtained through Mach number-wall surface temperature two-dimensional linear interpolation, wherein the wall surface temperature is the temperature of the previous time node, the pressure load corresponding to the Mach number of the current time is obtained through the linear interpolation, and an interpolation program is compiled through a python program and has a file name of interpolation. The flow chart is shown in fig. 4, the 283 time-state force Thermal coupling automatic calculation of the full section is completed, a solver "Thermal _ initial" is used for calculating a transient temperature field, a solver "Thermal _ couple" is used for calculating the Thermal-stress coupling, the calculation results are 283 moment temperature fields and 283 stress fields, and the file form is a calculation result file odb of abaqus.
And finally, constructing an optimus optimization model, and realizing optimization integration in optimus, wherein the optimization process is shown in FIG. 5, and a solver 'runAbaqus' is used for updating and calculating the force thermal coupling after the variable is changed every time. Firstly, an input and output file is analyzed, the file analysis is a key link for building an optimization platform, and the input file analysis tells optimus to design a variable t 1 、t 2 、t 3 、t 4 The variation range is 1 to 10, the interval is 0.5, the variation range is a series of discrete data, and the design variable thickness value combination is updated by setting an optimus optimization algorithm; and selecting the serious working condition of the thermal stress calculation on the full flight profile in the last step as an optimization input file. The output file analyzes and tells optimus the data to be extracted, and the constraint value and the objective function value are the maximum stress, the maximum strain, the maximum temperature value and the model weight of the model. And running an optimization flow and result analysis, reasonably selecting an optimization strategy provided by options, and performing sample point selection and automatic optimization calculation by software according to the upper and lower variable limits, the single variable quantity and the optimization strategy selected by a user for 284 times in the embodiment. The final calculation result is obtained as shown in FIG. 6, the constraint conditions are that the temperature, the stress and the strain are in a certain range, as shown in FIG. 7, the weight minimum time variable t 1 、t 2 、t 3 、 t 4 1, 2, 3.5 and 3.5 respectively, which are optimal solutions.
According to the optimization analysis, the structure optimization method based on the full-flight envelope force thermal coupling calculation is feasible, a high-efficiency and accurate processing method can be provided for practical engineering application, and the method can be better applied to engineering.
The structural optimization method based on the force-heat coupling calculation can realize the rapid automatic calculation of the transient temperature field at each moment on the full-flight envelope, the full-flight envelope force-heat coupling automatic calculation function with the structural temperature field and the static load as input, and the optimization calculation of multiple calculation states and multiple optimization strategies.
The structural optimization method based on force-heat coupling calculation can save a large amount of human resources, obtain more comprehensive distribution data of the temperature field and the stress field of the hypersonic flight vehicle, optimize and analyze the structure based on the calculation result of the temperature stress field of the full flight profile, increase the precision of optimal design and improve the efficiency of optimal design.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A structural optimization method based on force-thermal coupling calculation is characterized by comprising the following steps:
the method comprises the following steps of firstly, obtaining design variables to be optimized, constraint conditions and an optimization target;
secondly, establishing a geometric model according to the design variables, and establishing a finite element model according to the geometric model;
calculating a first temperature field at an initial moment according to the finite element model, and obtaining a first stress field after thermal stress deformation according to the first temperature field at the initial moment;
step four, constructing an optimus calculation model, calculating a second temperature field and a second stress field of the force-heat coupling at each moment in the full-profile range, and including:
s401, constructing a first optimus calculation model, and calculating a second temperature field of each moment in a full-profile range, wherein the temperature field obtained by calculation at the last moment is used as a predefined field of the current calculation moment;
s402, constructing a second optimus calculation model, and calculating a force-heat coupling second stress field at each moment in the full-profile range, wherein a temperature field obtained by calculation at the current moment is used as a predefined field for force-heat coupling calculation at the current moment;
and fifthly, constructing an optimus optimization model, loading the second temperature field and the second stress field into the optimus optimization model, and calculating the optimal solution of the design variables.
2. The method for structural optimization based on force-thermal coupling calculation according to claim 1, wherein in step one, the design variables include: aircraft skin thickness, air inlet duct wallboard thickness, spray pipe inner wall thickness, support frame web thickness, wing rib web thickness.
3. The structural optimization method based on force-heat coupling calculation according to claim 2, wherein in step one, the constraints of deformation, stress and model maximum temperature are within preset ranges, and the optimization goal is the lightest weight.
4. The method for structural optimization based on force-heat coupling calculation according to claim 3, wherein in the second step, the building a geometric model according to the design variables and building a finite element model according to the geometric model includes:
establishing a geometric model according to the design variables;
and carrying out mesh division on the geometric model, wherein the thin-wall structure uses shell units, the beam structure uses beam units, and corresponding material attributes are configured for each part to obtain a finite element model.
5. The method of claim 4, wherein the material properties include density, modulus of elasticity, specific heat capacity, coefficient of thermal expansion, and material plasticity parameters.
6. The method for structural optimization based on force-thermal coupling calculation according to claim 5, wherein in step three, the calculating the first temperature field at the initial time according to the finite element model comprises:
s301, obtaining a heat flow density load of the finite element model;
s302, setting an initial moment, loading the heat flow density load of the initial moment onto the finite element model, and performing transient temperature calculation in a finite element abaqus to obtain a first temperature field of the initial moment of the finite element model.
7. The method for structural optimization based on force-thermal coupling calculation according to claim 6, wherein in step three, the obtaining the first stress field after thermal stress deformation according to the first temperature field at the initial time comprises:
s303, taking the first temperature field as a calculated predefined field;
s304, setting an initial moment, loading the aerodynamic force load of the initial moment on the finite element model, and carrying out force-thermal coupling calculation in the finite element abaqus to obtain a first stress field of the initial moment of the finite element model.
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