CN107391891A - A kind of high aspect ratio wing Optimization Design based on Model Fusion method - Google Patents

A kind of high aspect ratio wing Optimization Design based on Model Fusion method Download PDF

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CN107391891A
CN107391891A CN201710790069.2A CN201710790069A CN107391891A CN 107391891 A CN107391891 A CN 107391891A CN 201710790069 A CN201710790069 A CN 201710790069A CN 107391891 A CN107391891 A CN 107391891A
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CN107391891B (en
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龙腾
汪艳
刘莉
李鑫
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Beijing Institute of Technology BIT
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Abstract

The present invention discloses a kind of high aspect ratio wing Optimization Design based on Model Fusion method, belongs to aircraft global optimization design field.The present invention will optimize the Optimized model for being divided into structure subject and system-level Optimized model according to demand, and Complex Constraints are handled using penalty function method；High and low precision pneumatic structure model of coupling is established using pneumatic structure Coupling method technology；Generate high and low precision sample point respectively using test design method；Call high and low precision structure model of coupling to obtain high and low precision sample information respectively and store；Using Model Fusion method, agent model is established with low accuracy model information fusion by high-precision；Solution is optimized with optimization method based on current agent model, judge whether optimum results are credible according to the difference of the true response at optimal solution and the agent model value based on Model Fusion method, insincere, return reconfigures Fusion Model and optimizes solution, it is credible then to export optimal design result, complete optimization design.

Description

A kind of high aspect ratio wing Optimization Design based on Model Fusion method
Technical field
The present invention relates to a kind of high aspect ratio wing Optimization Design based on Model Fusion method, it is total to belong to aircraft Body design optimizing field.
Background technology
High aspect ratio wing has the characteristics that lift-drag ratio is big, wing internal volume is big, is widely used in High Altitude UAV, the sun In the aircraft such as energy aircraft, large-scale intercontinental passenger plane.This kind of aircraft is in flight course, and high aspect ratio wing is by aerodynamic loading Influence, recurring structure deformation, influence of the amplitude of deformation to aeroperformance be fairly obvious.Therefore, high aspect ratio wing is carried out Need to consider pneumatic structure coupled problem during analysis design., can be by hydrodynamics and structural capacity for pneumatic structure coupled problem Learn and independently solved as single subject, and interdisciplinary data interaction is realized by software scheduling techniques, iterative realizes coupling point Analysis.To improve coupling analysis precision, frequently with high accuracy analysis method such as Fluid Mechanics Computation method (CFD) and finite element analysis Method (FEA) carries out analysis and solution to two single subjects respectively.However, high accuracy analysis model is improving analysis precision and credible Also the problem of calculating is time-consuming is brought while spending, although computer nowadays software and hardware technology has had significant progress, High accuracy analysis model is called to complete an iteration solution still extremely time-consuming.Such as completed once using CFD model pneumatic imitative True analysis needs a few hours even tens of hours.High aspect ratio wing optimization design is also the process to iterate, is being optimized Thousands of times are generally required in journey and calls high-precision model of coupling, further increases design cost, causes optimization design efficiency It is very low.
In order to better illustrate technical scheme, the pneumatic structure Coupling method technology being applied to is carried out below It is specific to introduce.
Pneumatic structure Coupling method technology：
With the increase of wing aspect ratio, the flexibility of wing is continuously increased, the coupling between its aeroperformance and structural behaviour It is also more obvious to close phenomenon.And the key of pneumatic structure Coupling method technology is then the pneumatic information transmission between structure subject. In existing ripe pneumatic structure Coupling method technology, often realize aerodynamic analysis result to structure using three-dimensional interpolation method Subject transmission, while according to the coordinate at control point on the front and rear edge of wing after deformation determine to update the geometric shape of wing, weight Pneumatic subject analysis is newly carried out, completes transmission of the structure subject analysis result to pneumatic subject.On the other hand, in pneumatic structure coupling Build jointly in mould, the density degree of pneumatic subject grid often controls the calculating cost and model essence of whole model of coupling Degree.Mesh-density is increased, analysis model precision can be improved, but can also increase calculating cost simultaneously.On the contrary, reduce mesh-density Computational accuracy can then be reduced and reduce calculating cost.
The flow chart of pneumatic structure model of coupling is as shown in figure 1, specific method step is as follows：
Step 1. uses the model parameterization technology based on UG secondary development, foundation/renewal wing parameterized model.Geometry The parameter of model parameterization includes geometry designs variable aspect ratio, contraction coefficient, angle of sweep, aerofoil profile parameter and for quantificational expression The coordinate information at the wing front and rear edge position control point of construction profile deflection.Geometric shape file is exported after the completion of parametrization to use Used in subsequent analysis, generally step forms or igs forms.
Step 2. establishes aerodynamic analysis model using CFD.Input geometric shape file, aerodynamic analysis work information include horse Conspicuous number, the angle of attack, output aerodynamic analysis result include lift, Resistance Pressure information and aerodynamic force distribution file.It can be entered using Gambit Row grid drawing, aerodynamic analysis solution is carried out using Fluent.
Step 3. establishes structure subject analysis model using FEA methods, carries out pre-treatment using Patran, Nastran makees For post processing.Geometric shape file is inputted, material properties are carried out using PCL language, cell attribute definition and aerodynamic force load Deng correlation analysis optimal setting.The SQP optimizers carried in Nastran can realize that structure subject optimizes.Final output structure point Analysis structure includes maximum stress and the coordinate information at maximum displacement and wing front and rear edge control point.
If step 4. analysis for the first time repeats then by the control point coordinate information input model parameterized module after deformation Step 2,3,4, if non-first time is analyzed, relative shift is calculated, shown in relative shift η calculating such as formula (1).When relative Displacement is less than 0.01, and iteration terminates, and exports now aerodynamic analysis result, including lift-drag ratio, quality, maximum stress, dominant bit Shifting and the optimum results of structure subject variable；When relative shift is more than 0.01, then repeat step 1,2,3,4, until relative Displacement is less than 0.01, and iteration terminates.
I represents ith analysis in formula (1), and i-1 represents the last analysis of ith analysis.
The content of the invention
The problem of cost is too high is calculated during in high aspect ratio wing process of optimization, considering pneumatic structure coupling, A kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed by the invention, technical problems to be solved are In the case where ensureing precision, consider that pneumatic structure coupled problem realizes the effectively optimizing design of high aspect ratio wing, have such as Lower advantage：Effective integration is carried out to high and low precision analysis model information using Model Fusion method, makes full use of low accuracy model The precision of information assurance Fusion Model, the call number of high accuracy analysis model is reduced, so as to reduce calculating cost, improve great Zhan Optimization design efficiency of the string than wing.
The purpose of the present invention is achieved through the following technical solutions.
A kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed by the invention, will according to design Selection initial reference aerofoil profile and wing associated shape parameter are asked, determines design conditions；The excellent of structure subject is established according to demand Change model and system-level Optimized model, and use penalty function method processing Complex Constraints；Built using pneumatic structure Coupling method technology Found high and low precision high aspect ratio wing pneumatic structure model of coupling；Generate high and low precision respectively using test design method Sample point；High and low precision high aspect ratio wing pneumatic structure model of coupling is called to obtain high and low precision sample information respectively And store；Using Model Fusion method, merged high-precision with low accuracy model information, establish agent model implementation model Precision and the comprehensive coordination for calculating cost；Solution is optimized using optimization method based on current agent model, according to optimal solution The true response at place judges whether optimum results are credible with the difference of the agent model value based on Model Fusion method, if can not Believe that then return reconfigures Fusion Model and optimize solution, optimal design result is exported if credible, that is, complete to consider pneumatically Structure Coupling problem realizes the effectively optimizing design of high aspect ratio wing.
A kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed by the invention, including following step Suddenly：
Step 1：According to design requirement, initial reference aerofoil profile and wing associated shape parameter are selected, determines design conditions.
Described design conditions include Mach number and the angle of attack.
Step 2：The Optimized model of structure subject and system-level Optimized model are established according to demand.
Step 2.1：The Optimized model of structure subject is established according to demand.
In order to while structural strength is ensured, quality be reduced to greatest extent, to machine during structural analysis Each construction package of the wing carries out dimensionally-optimised.Design variable include skin thickness, web thickness, flange radius, web thickness, Flange radius；Optimization aim is that architecture quality is minimum；Constraints constrains to meet that maximum stress constraint deforms with maximum displacement. The optimization of structure subject is realized in structure subject analysis model.
Step 2.2：System-level Optimized model is established according to demand.
It is design variable that geometry design parameter is selected in system-level optimization, described design variable include aspect ratio, contraction coefficient, Angle of sweep, and its bound is determined according to demand；Maximum, the minimum optimization aim of architecture quality, constraints bag with lift-drag ratio It is constant less than displacement allowable and wing area less than allowable stress, structure maximum displacement to include structure maximum stress.
Step 3：High and low precision high aspect ratio wing pneumatic structure coupling point is established using pneumatic structure Coupling method technology Analyse model.Pneumatic subject mesh-density is the principal element for calculating cost and computational accuracy, therefore is made in aerodynamic analysis model Low precision analysis model is established with coarse grid, high-precision analysis model is established using refined net.
Realize that computational accuracy with calculating the coordination of cost, is built by the density degree of pneumatic subject mesh-density in step 3 Found the pneumatic structure model of coupling of high and low precision.
Step 4：N is generated respectively using test design methodhIndividual high-precision sample point and NlIndividual low precision sample point.Sample Point quantity and system-level optimization design variable dimension nvIt is related.Need to include all high-precision samples in wherein low precision sample point Point.
To realize the high efficiency for the high aspect ratio wing optimization design for considering pneumatic structure coupled problem, described in step 4 Test design method preferably use Latin hypercube experimental design method.
Sample point quantity preferably takes N depending on theory analysis, experiment or empirical valueh=(nv+3)*(nv+ 2), 4Nh≤Nl ≤6Nh。
Step 5：High and low precision high aspect ratio wing pneumatic structure model of coupling in invocation step 3, obtain step 4 In NhAnd NlModel response at sample point, store high and low precision sample point information.
Step 6:High and low precision sample point information is merged using Model Fusion method, establishes agent model.It is described Agent model be the Fusion Model y that is made up of the agent model of correction model and the agent model of error models(x)。
The concrete methods of realizing of step 6 is as follows：
Step 6.1：According to high-precision sample and corresponding low precision sample information, low essence is obtained using least square method Shown in the modifying factor such as formula (2) for spending high aspect ratio wing pneumatic structure coupling analysis sample point：
Wherein：NhFor high-precision high aspect ratio wing pneumatic structure coupling analysis sample point number；yh(xi) it is high-precision gas The response of dynamic structure coupling analysis model, yl(xi) be low precision pneumatic structure model of coupling response, described sound It should be worth including lift-drag ratio, architecture quality, structure maximum stress, structure maximum displacement；ρ0、ρ1For the coupling point of low precision pneumatic structure The modifying factor of model sample point is analysed, each response has modifying factor corresponding to oneself.
Step 6.2：Using the modifying factor of the low precision pneumatic structure model of coupling sample point in step 6.1 to institute There is low precision pneumatic structure model of coupling sample point to be modified, based on revised low precision pneumatic structure coupling analysis Model sample information uses Kriging method construct agent models, the correction model of low precision pneumatic structure model of coupling yl s(x) it is expressed as：
yl s(x)=ρ0+ρ1yl(x) (3)
Wherein yl(x) it is the response of low precision pneumatic structure model of coupling sample point, using formula (3) to all low Precision pneumatic structure model of coupling sample points evidence, which is modified, obtains repairing for low precision pneumatic structure model of coupling Positive model yl s(x).Low precision pneumatic structure model of coupling correction model y is completed using Kriging methodsl s(x) agency Model ys s(x) construct.
Step 6.3：High-precision pneumatic structure coupling analysis model sample point and low precision in step 6.2 in calculation procedure 5 Error amount δ (x between the correction model of pneumatic structure model of couplingi), error amount δ (xi) obtained by formula (4) calculating：
δ(xi)=yh(xi)-yl s(xi)=yh(xi)-[ρ0+ρ1yl(xi)]) i=1,2,3 ... Nh) (4)
Based on control information δ (xi), using Kriging methods, complete the agent model δ of error models(x) construction.
Step 6.4：Build the agent model y by the correction model in step 6.2s s(x) with step 6.3 in error model Agent model δs(x) the Fusion Model y of compositions(x), as shown in formula (5)：
ys(x)=ys s(x)+δs(x) (5)
Described Fusion Model ys(x) it is the agent model of high-precision pneumatic structure coupling analysis model.
Step 7：Based on the Fusion Model y established in step 6s(x), using the complexity in penalty function process problem about Beam, system optimization problem solving is carried out using optimized algorithm, obtains being based on present fusion model ys(x) optimal solution
Shown in described penalty function such as formula (6)：
F (x)=f (x)+MP (x) M ＞ 0
Wherein：F (x) is the optimization aim after processing, and f (x) is original optimization aim, and M is penalty factor, and P (x) is constraint Degree of running counter to, gi(x) it is inequality constraints, hi(x) it is equality constraint, m is inequality constraints number, and l is constraint total number.
The preferred genetic algorithm of system optimization problem solving is carried out in step 7 using optimized algorithm to solve.
Step 8:High-precision high aspect ratio wing pneumatic structure model of coupling in invocation step 3, obtain step 7 In agent model optimal solutionThe true response at place.Calculate the true response of optimal solution and the difference of agent model value Value, judges whether the optimum results are credible according to size of the difference.Return to step 4 if insincere, increase low precision high aspect ratio Wing aerodynamic structure coupling analysis model sample point quantity, repeat step 5,6,7,8, until believable optimum results are obtained, if It is credible then to export optimal design result, that is, complete to consider that the effectively optimizing of the high aspect ratio wing of pneumatic structure coupled problem is set Meter.
Beneficial effect：
Need to consider that pneumatic structure coupled problem causes process of optimization to calculate when the 1st, designing for high aspect ratio wing The problem of cost is difficult to bear, a kind of high aspect ratio wing optimization design side based on Model Fusion method disclosed by the invention Method, realize analysis model precision with calculating the comprehensive coordination of cost by mesh density control.
2nd, a kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed by the invention, uses model Fusion method merges high and low accuracy model efficient information, while design accuracy requirement is met, reduces high accuracy analysis mould The calling amount of type, reduce and calculate cost, improve the design efficiency of high aspect ratio wing.
3rd, a kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed by the invention, using penalizing letter Several modes is handled Complex Constraints problem, realizes the succinct of process of optimization and facility.
4th, a kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed by the invention, use are optimal The reliability that the difference of true response and the agent model value of solution carries out optimal result judges, complete the renewal of Optimizing Flow with Iteration.
5th, a kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed by the invention, utilize Kriging agent model methods, the construction of the agent model of correction model and the agent model of error model is efficiently completed, is entered And high and low accuracy model information is set more effectively to merge.
6th, a kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed by the invention, uses heredity Algorithm optimizes solution, can avoid occurring the situation without solution in Optimization Solution, improve the solution of Optimum design of engineering structure problem Feasibility.
Brief description of the drawings
Fig. 1 is high aspect ratio wing pneumatic structure coupling analysis flow chart；
Fig. 2 is the high aspect ratio wing Optimization Design flow chart for considering pneumatic structure coupling；
Fig. 3 is the high and low precision grid comparison diagram of pneumatic subject,
Wherein Fig. 3 a are high accuracy analysis model meshes, and Fig. 3 b are low precision analysis model meshes；
Fig. 4 is Model Fusion method flow diagram；
Embodiment
In order to which technical scheme and advantage is better described, set below by the optimization of specific high aspect ratio wing Example is counted, and the present invention will be further described with form with reference to accompanying drawing, embodiment is as follows.
A kind of high aspect ratio wing Optimization Design based on Model Fusion method disclosed in the present embodiment, flow chart is such as Shown in Fig. 2, specific implementation step is as follows：
Step 1：It is flight Mach number Ma=that laminar flow airfoil NACA64A816, which is chosen, as the initial aerofoil profile of benchmark, design conditions 0.64, angle of attack=2 ° wing shapes are determined by the initial value of system variable, specific as shown in table 2.
Step 2：The Optimized model of structure subject and system-level Optimized model are established according to demand.
Step 2.1：The Optimized model of structure subject is established according to demand.
Each construction package progress to wing in the Optimized model of structure subject is dimensionally-optimised.Select each wing box Skin thickness (Tskin), the web thickness (T of each ribrib), the flange radius (R of each ribrib), the web of each spar Thickness (Tspar), the flange radius (R up and down of each sparspar), as structure subject optimization design variable.Constraints includes Structure maximum stress σmaxLess than allowable stress 100MPa, structure maximum displacement δmaxLess than displacement 900mm allowable.Structure optimization mesh The architecture quality W for being designated as wing is minimum.The optimization of structure subject is realized in structure subject analysis model.Model of structural optimization is such as Shown in following formula (7).
Wherein, xstrucFor structure subject optimization design variable, xstruc lbAnd xstruc ubRespectively structure design variable is upper Limit and lower limit, design variable value are as shown in table 1.
The structure design variable of table 1 and excursion
Step 2.2：System-level Optimized model is established according to demand.
It is design variable that geometry design parameter is selected in system-level optimization, and described geometry design parameter includes aspect ratio, root Tip ratio, angle of sweep, and its bound is determined according to demand, as shown in table 2；To tie lift-drag ratio D/L maximums, architecture quality W is minimum For optimization aim, constraints includes structure maximum stress σmaxLess than allowable stress 100MPa, structure maximum displacement δmaxIt is less than Displacement 900mm and wing area allowable it is constant it is constant be 50.17m2.Shown in system-level Optimized model such as formula (8).
Min F (X)=1/2 × Cweight+1/2×CD/L
s.t.σmax≤100Mpa (8)
δmax≤900mm
Xlb≤X≤Xub
S=50.17m2
F (X) is complex optimum target, obtained by two optimization aim architecture quality W and lift-drag ratio D/L linear weighted functions, The weight of two optimization aims is identical in this example is taken as 1/2.Because the order of magnitude of each target differs, using first The architecture quality W of beginning wingbaselineWith the lift-drag ratio (D/L) of initial wingbaselineRespectively to optimization aim architecture quality with rising Resistance ratio does normalized, the object function response C after being normalizedweightAnd CD/L.X is design variable, XlbAnd XubPoint Not Wei design variable bound, specific value is as shown in table 2.
The system level design variable of table 2 and excursion
Step 3：High high aspect ratio wing aerodynamic structure coupling analysis model is established using pneumatic structure Coupling method technology With low precision high aspect ratio wing pneumatic structure model of coupling.In this step, adjusted and realized by grid drawing density The differentiation of high and low precision analysis model.In the present embodiment, high-precision mesh-density is twice of low precision, as shown in Figure 3. In structure subject analysis model, the FEM model cell attribute definition of structure subject is as shown in table 3, is carried using Nastran SQP optimizers complete structure subject optimization, its Optimized model be step 2.1 in structure subject Optimized model described in.
The FEM model cell attribute of table 3
Step 4：High-precision model sample point and low accuracy model sample are generated using Latin hypercube experimental design method Point.In the present invention, calculate cost and time calculating is calculated with CPU.By experiment statisticses, each high accuracy analysis model needs about 20 minutes, the calculating cost of each low precision analysis model was about 3 minutes.30 high-precision samples are generated for Model Fusion method This point and 130 low precision sample points.In order to carry out efficiency comparative, while generate 50 high-precision sample points and (calculate cost about For 30 high accuracy analysis and 130 low precision analysis sums) it is used to construct the agent model using conventional method.
It is direct for Kriging methods are used alone in the implementation case that above-mentioned use conventional method constructs agent model Construct the agent model of high-precision high aspect ratio wing pneumatic structure model of coupling.
Step 5：High and low precision high aspect ratio wing pneumatic structure model of coupling in invocation step 3, obtain step 4 In 30 high-precision sample points and 130 low precision sample points at model response, store high and low precision high aspect ratio machine Wing pneumatic structure model of coupling sample point information.In order to carry out efficiency comparative, 50 need to be obtained simultaneously and is based on for construction Model response at the high-precision sample point of the agent model of conventional method.
Step 6:Using Model Fusion method by 30 high-precision sample point information in step 5 and 130 low precision samples This information is merged, and establishes the high-precision great Zhan strings wing aerodynamic structure coupling analysis model based on Model Fusion method Agent model.Its particular flow sheet is as shown in Figure 4.It is meanwhile direct based on conventional method using 50 high-precision sample point information Construct the agent model of high-precision great Zhan strings wing aerodynamic structure coupling analysis model.
Step 7：The agent model that Model Fusion method is established and conventional method method structure are utilized based on what step 6 was established The agent model made, is optimized using genetic algorithm.The mode of penalty function is used for the Complex Constraints in the optimization problem Handled, penalty factor is taken as 1000.Respectively obtain optimal solution based on Model Fusion method and based on conventional method most Excellent solution.
Step 8:High-precision high aspect ratio wing pneumatic structure model of coupling in invocation step 3, obtain step 7 In agent model optimal solutionThe true response at place.Calculate the true response of optimal solution and the difference of agent model value Value, judges whether the optimum results are credible according to size of the difference.Return to step 4 if insincere, increase low precision high aspect ratio Wing aerodynamic structure coupling analysis model sample point quantity, repeat step 5,6,7,8, until believable optimum results are obtained, if It is credible then to export optimal design result, that is, complete to consider that the effectively optimizing of the high aspect ratio wing of pneumatic structure coupled problem is set Meter.
Statistical system optimum results are as shown in table 4, and structure subject optimum results are as shown in table 5.
The three-dimensional wing system optimization result of table 4
Table 4 is observed, contrast uses the Optimum Design Results of two methods, it is possible to find lift-drag ratio has smaller improvement, but structure Mass change is obvious.Using the Optimization Design in the present invention, quality reduces by 54%, and matter in the optimum results of conventional method Amount only reduces by 4%.The use of the complex optimum desired value after the normalization after the inventive method is 0.7258, much smaller than identical meter It is counted as the optimum results of this lower conventional method.Simultaneously using real goal value during Optimization Design of the present invention and agent model value Difference it is smaller, illustrate the present invention Optimization Design there is higher precision.Contrasted by experimental result, draw this hair For bright method compared to conventional method, not only model accuracy is higher in the case of identical calculations cost, and optimizes with more preferable Design result.Therefore, using a kind of high aspect ratio wing Optimization Design based on Model Fusion method proposed by the present invention Precision can ensured simultaneously by carrying out high aspect ratio wing optimization design, the calling amount of high accuracy analysis model be reduced, so as to drop Low calculating cost, improve the optimization design efficiency of high aspect ratio wing.
The three-dimensional wing structure optimization result of table 5
Visible according to foregoing specific high aspect ratio wing Optimal Example analysis, the present invention can realize expected invention mesh , compared to traditional high aspect ratio wing Optimization Design, the present invention is favorably improved high aspect ratio wing optimization design As a result with designing quality；On the other hand, it is related to the optimization problem of high aspect ratio wing high accuracy analysis model, the present invention can also be big The optimization efficiency improved greatly, optimization design cost is reduced, shorten the optimization design cycle.
Above-described specific descriptions, the purpose, technical scheme and beneficial effect of invention are carried out further specifically It is bright, the specific embodiment that the foregoing is only the present invention is should be understood that, for explaining the present invention, is not used to limit this The protection domain of invention, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc. all should Within protection scope of the present invention.

Claims (7)

  1. A kind of 1. high aspect ratio wing Optimization Design based on Model Fusion method, it is characterised in that：Comprise the following steps,
    Step 1：According to design requirement, initial reference aerofoil profile and wing associated shape parameter are selected, determines design conditions；
    Step 2：The Optimized model of structure subject and system-level Optimized model are established according to demand；
    Step 3：High and low precision high aspect ratio wing pneumatic structure coupling analysis mould is established using pneumatic structure Coupling method technology Type；Pneumatic subject mesh-density is the principal element for calculating cost and computational accuracy, therefore using thick in aerodynamic analysis model Grid establishes low precision analysis model, and high-precision analysis model is established using refined net；
    Step 4：N is generated respectively using test design methodhHigh-precision sample point and NlIndividual low precision sample point；Sample point quantity With system-level optimization design variable dimension nvIt is related；Need to include all high-precision sample points in wherein low precision sample point；
    Step 5：High and low precision high aspect ratio wing pneumatic structure model of coupling in invocation step 3, obtain the N in step 4h And NlModel response at sample point, store high and low precision sample point information；
    Step 6:High and low precision sample point information is merged using Model Fusion method, establishes agent model；Described generation Reason model is the Fusion Model y being made up of the agent model of correction model and the agent model of error models(x)；
    Step 7：Based on the Fusion Model y established in step 6s(x), using the Complex Constraints in penalty function process problem, use Optimized algorithm carries out system optimization problem solving, obtains being based on present fusion model ys(x) optimal solution
    Shown in described penalty function such as formula (6)：
    <mrow> <mtable> <mtr> <mtd> <mtable> <mtr> <mtd> <mrow> <mi>F</mi> <mrow> <mo>(</mo> <mi>x</mi> <mo>)</mo> </mrow> <mo>=</mo> <mi>f</mi> <mrow> <mo>(</mo> <mi>x</mi> <mo>)</mo> </mrow> <mo>+</mo> <mi>M</mi> <mi>P</mi> <mrow> <mo>(</mo> <mi>x</mi> <mo>)</mo> </mrow> </mrow> </mtd> <mtd> <mrow> <mi>M</mi> <mo>&gt;</mo> <mn>0</mn> </mrow> </mtd> </mtr> </mtable> </mtd> </mtr> <mtr> <mtd> <mrow> <mi>P</mi> <mrow> <mo>(</mo> <mi>x</mi> <mo>)</mo> </mrow> <mo>=</mo> <munderover> <mi>&amp;Sigma;</mi> <mrow> <mi>i</mi> <mo>=</mo> <mn>1</mn> </mrow> <mi>m</mi> </munderover> <mrow> <mo>(</mo> <mi>max</mi> <mo>(</mo> <mrow> <mn>0</mn> <mo>,</mo> <msub> <mi>g</mi> <mi>i</mi> </msub> <msup> <mrow> <mo>(</mo> <mi>x</mi> <mo>)</mo> </mrow> <mn>2</mn> </msup> </mrow> <mo>)</mo> <mo>)</mo> </mrow> <mo>+</mo> <munderover> <mi>&amp;Sigma;</mi> <mrow> <mi>i</mi> <mo>=</mo> <mi>m</mi> <mo>+</mo> <mn>1</mn> </mrow> <mi>l</mi> </munderover> <msub> <mi>h</mi> <mi>i</mi> </msub> <msup> <mrow> <mo>(</mo> <mi>x</mi> <mo>)</mo> </mrow> <mn>2</mn> </msup> </mrow> </mtd> </mtr> </mtable> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>1</mn> <mo>)</mo> </mrow> </mrow>
    Wherein：F (x) is the optimization aim after processing, and f (x) is original optimization aim, and M is penalty factor, and P (x) runs counter to for constraint Degree, gi(x) it is inequality constraints, hi(x) it is equality constraint, m is inequality constraints number, and l is constraint total number；
    Step 8：High-precision high aspect ratio wing pneumatic structure model of coupling in invocation step 3, obtain in step 7 The optimal solution of agent modelThe true response at place；Calculate the true response of optimal solution and the difference of agent model value, root Judge whether the optimum results are credible according to size of the difference；Return to step 4 if insincere, increase low precision high aspect ratio wing gas Dynamic structure coupling analysis model sample point quantity, repeat step 5,6,7,8, until believable optimum results are obtained, if credible Optimal design result is exported, that is, completes to consider the effectively optimizing design of the high aspect ratio wing of pneumatic structure coupled problem.
  2. 2. a kind of high aspect ratio wing Optimization Design based on Model Fusion method as claimed in claim 1, its feature It is：Step 2 concrete methods of realizing is,
    Step 2.1：The Optimized model of structure subject is established according to demand；
    In order to while structural strength is ensured, quality be reduced to greatest extent, to wing during structural analysis Each construction package carries out dimensionally-optimised；Design variable includes skin thickness, web thickness, flange radius, web thickness, flange Radius；Optimization aim is that architecture quality is minimum；Constraints constrains to meet that maximum stress constraint deforms with maximum displacement；Structure The optimization of subject is realized in structure subject analysis model；
    Step 2.2：System-level Optimized model is established according to demand；
    It is design variable that geometry design parameter is selected in system-level optimization, and described design variable includes aspect ratio, contraction coefficient, sweepback Angle, and its bound is determined according to demand；Maximum, the minimum optimization aim of architecture quality with lift-drag ratio, constraints include knot Structure maximum stress is less than allowable stress, structure maximum displacement is less than displacement allowable and wing area is constant.
  3. 3. a kind of high aspect ratio wing Optimization Design based on Model Fusion method as claimed in claim 1 or 2, it is special Sign is：Computational accuracy is realized by the density degree of pneumatic subject mesh-density in step 3 and calculates the coordination of cost, is established The pneumatic structure model of coupling of high and low precision.
  4. 4. a kind of high aspect ratio wing Optimization Design based on Model Fusion method as claimed in claim 3, its feature It is：The concrete methods of realizing of step 6 is as follows：
    Step 6.1：According to high-precision sample and corresponding low precision sample information, it is big to obtain low precision using least square method Shown in the modifying factor such as formula (2) of aspect ratio wing aerodynamic structure coupling analysis sample point：
    <mrow> <mi>min</mi> <mi> </mi> <mi>L</mi> <mrow> <mo>(</mo> <msub> <mi>&amp;rho;</mi> <mn>0</mn> </msub> <mo>,</mo> <msub> <mi>&amp;rho;</mi> <mn>1</mn> </msub> <mo>)</mo> </mrow> <mo>=</mo> <munderover> <mo>&amp;Sigma;</mo> <mrow> <mi>i</mi> <mo>=</mo> <mn>1</mn> </mrow> <msup> <mi>N</mi> <mi>h</mi> </msup> </munderover> <msup> <mrow> <mo>&amp;lsqb;</mo> <msub> <mi>&amp;rho;</mi> <mn>0</mn> </msub> <mo>+</mo> <msub> <mi>&amp;rho;</mi> <mn>1</mn> </msub> <msup> <mi>y</mi> <mi>l</mi> </msup> <mrow> <mo>(</mo> <msub> <mi>x</mi> <mi>i</mi> </msub> <mo>)</mo> </mrow> <mo>-</mo> <msup> <mi>y</mi> <mi>h</mi> </msup> <mrow> <mo>(</mo> <msub> <mi>x</mi> <mi>i</mi> </msub> <mo>)</mo> </mrow> <mo>&amp;rsqb;</mo> </mrow> <mn>2</mn> </msup> <mo>,</mo> <mrow> <mo>(</mo> <mi>i</mi> <mo>=</mo> <mn>1</mn> <mo>,</mo> <mn>2</mn> <mo>,</mo> <mn>3</mn> <mo>...</mo> <msup> <mi>N</mi> <mi>h</mi> </msup> <mo>)</mo> </mrow> <mo>-</mo> <mo>-</mo> <mo>-</mo> <mrow> <mo>(</mo> <mn>2</mn> <mo>)</mo> </mrow> </mrow>
    Wherein：NhFor high-precision high aspect ratio wing pneumatic structure coupling analysis sample point number；yh(xi) it is high-precision pneumatic knot The response of structure model of coupling, yl(xi) be low precision pneumatic structure model of coupling response, described response Including lift-drag ratio, architecture quality, structure maximum stress, structure maximum displacement；ρ0、ρ1For low precision pneumatic structure coupling analysis mould The modifying factor of type sample point, each response have modifying factor corresponding to oneself；
    Step 6.2：Using the modifying factor of the low precision pneumatic structure model of coupling sample point in step 6.1 to all low Precision pneumatic structure model of coupling sample point is modified, based on revised low precision pneumatic structure model of coupling Sample information uses Kriging method construct agent models, the correction model y of low precision pneumatic structure model of couplingl s(x) It is expressed as：
    yl s(x)=ρ0+ρ1yl(x) (3)
    Wherein yl(x) it is the response of low precision pneumatic structure model of coupling sample point, using formula (3) to all low precision Pneumatic structure model of coupling sample points evidence is modified the amendment mould for obtaining low precision pneumatic structure model of coupling Type yl s(x)；Low precision pneumatic structure model of coupling correction model y is completed using Kriging methodsl s(x) agent model ys s(x) construct；
    Step 6.3：High-precision pneumatic structure coupling analysis model sample point and low precision in step 6.2 are pneumatic in calculation procedure 5 Error amount δ (x between the correction model of structure coupling analysis modeli), error amount δ (xi) obtained by formula (4) calculating：
    δ(xi)=yh(xi)-yl s(xi)=yh(xi)-[ρ0+ρ1yl(xi)] (i=1,2,3 ... Nh) (4)
    Based on control information δ (xi), using Kriging methods, complete the agent model δ of error models(x) construction；
    Step 6.4：Build the agent model y by the correction model in step 6.2s s(x) generation of the error model and in step 6.3 Manage model δs(x) the Fusion Model y of compositions(x), as shown in formula (5)：
    ys(x)=ys s(x)+δs(x) (5)
    Described Fusion Model ys(x) it is the agent model of high-precision pneumatic structure coupling analysis model.
  5. 5. a kind of high aspect ratio wing Optimization Design based on Model Fusion method as claimed in claim 4, its feature It is：To realize the high efficiency for the high aspect ratio wing optimization design for considering pneumatic structure coupled problem, the examination described in step 4 Test design method and use Latin hypercube experimental design method.
  6. 6. a kind of high aspect ratio wing Optimization Design based on Model Fusion method as claimed in claim 5, its feature It is：Sample point quantity takes N depending on theory analysis, experiment or empirical value in step 4h=(nv+3)*(nv+ 2), 4Nh≤Nl ≤6Nh。
  7. 7. a kind of high aspect ratio wing Optimization Design based on Model Fusion method as claimed in claim 6, its feature It is：Carrying out system optimization problem solving using optimized algorithm in step 7 selects genetic algorithm to solve.
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