CN107391858A - A kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount - Google Patents
A kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount Download PDFInfo
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Abstract
The invention provides a kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount, Dependence Problem of the program for different incoming fast pressing test data extrapolation methods to stagnation temperature stagnation pressure independent control wind tunnel test capacity of equipment, the independent change stagnation pressure wind tunnel test methods that can be realized using most wind-tunnel, obtain the wind tunnel test data that different Reynolds number combines with incoming ram compression, the difficulty of wind tunnel test is greatly reduced, preparatory period and cost, eliminate dependence of the model static elasticity deformation effect amendment to wind-tunnel, carry out corresponding amendment experiment for all kinds of conventional wind-tunnel and technical support is provided.It is high with calculating cost for the time in numerical simulation/model deformation measurement integrated processes, the problem of static elasticity deformation effect can not be analyzed in real time, using the method for algebraic equation solving, the quick separating of reynolds number effect and static elasticity deformation effect effect can be realized, so as to analyze influence amount of the static elasticity deformation to aerodynamic characteristics in real time.
Description
Technical field
It is especially a kind of to obtain the deformation of wind tunnel model aeroelastic effect the present invention relates to aircraft wind tunnel test field
The method of influence amount.
Background technology
In aircraft wind tunnel test, designer it is expected to obtain aerodynamic force number of the dummy vehicle under rigid profile state
According to.But due to the effect of wind-tunnel incoming aerodynamic loading, aeroelastic effect deformation can occur for model wing, so as to change around model
Flow Field, and then change the aerodynamic load that bears of wind tunnel model.Meanwhile wind-tunnel balance measurement is that model is outer in deformation
Had differences between aerodynamic load data under shape, with desired rigid profile load.Therefore, when model is deposited in experiment process
In larger aeroelastic effect deformation, wind tunnel test packet can be caused to contain the systematic error that can not be ignored, and cause wind-tunnel
The reduction of test data accuracy, so as to influence the global design performance of aircraft and design objective.For example, Boeing supersonic speed
Transporter model langley center NTF equipment carry out high Reynola number wind tunnel experiment when, model wing static elasticity deformation inductdion
Wingtip section torsion angle has reached -2.2 °, thus causes resistance coefficient to reduce nearly 50 resistances with respect to certain reference state maximum
Unit (each resistance unit is equal to 0.0001), greatly change the aerodynamic coefficient distribution curve of the model.And in great Zhan
String is more quiet than field, models such as the researchs of transporter model wind tunnel test, reynolds number effect wind tunnel test and CFD software verification and validation
Influence of the elastic deformation to aerodynamic characteristics further highlights, and has caused the pass of aerodynamic studies person in world wide
Note and attention, and carried out the amendment research of related static elasticity deformation effect amount.
At present, wind tunnel model aeroelastic effect deformation effect technology mainly has two major classes：One kind is to be based on the total pressure energy of stagnation temperature
Enough separately adjustable wind-tunnel facilities separate model static elasticity deformation effect from wind tunnel test；One kind is to utilize Numerical-Mode
Intend the influence amount to aerodynamic force with model deformation survey calculation model deformation.Wherein first method passes through separately adjustable wind-tunnel
Stagnation temperature and stagnation pressure, in the case where ensureing that other flow parameters are constant, carry out examination under conditions of a change wind-tunnel incoming ram compression q
Test, then obtain experiment number when incoming ram compression is zero (being deformed into zero) using the test data extrapolation under different incoming ram compressions
According to, and then the influence of correction model static elasticity deformation.But this method wind tunnel test equipment separately adjustable dependent on stagnation temperature stagnation pressure,
Possesses the high wind tunnel testing equipment only seldom several of this kind of ability in world wide at present, such as the NTF in the U.S. with Europe
ETW, the country do not have such testing equipment still.On the other hand, this kind of testing equipment adjusts the temperature of wind-tunnel using liquid nitrogen more, because
This wind tunnel test preparatory period is very long, and experimentation cost is high, and there is also use upper risk for data extrapolation result.And second
The wing that method is obtained first with model deformation measurement techniques in wind tunnel test deforms, and then utilizes deformation displacement data reconstruction
Mode shape after deformation, finally using method for numerical simulation, such as CFD, the front and rear aerodynamic load of computation model deformation, obtain
Model aeroelastic effect deforms the influence amount to aerodynamic coefficient.The method of numerical simulation/model deformation measurement has preferable
Calculating resolution, but the confidence level of correction result dependent on model deformation measure with deform Shape Reconstruction precision, and the time with
It is higher to calculate cost, the real-time analysis of data can not be realized.
Therefore, the present invention proposes a kind of technological process for obtaining wind tunnel model aeroelastic effect deformation effect amount, that is, pass through
Regulation wind tunnel operation stagnation pressure obtains the wind tunnel test data under different Reynolds number combines with incoming ram compression, then utilizes aerodynamic force number
Both influences are separated according to Reynolds number changing rule different from incoming ram compression, so as to quickly and easily be calculated
Aerodynamic coefficient variable quantity caused by static elasticity deformation.
The content of the invention
The purpose of the present invention, aiming at the deficiency present in prior art, and provide a kind of acquisition wind tunnel model pneumostatic
The method of dynamic elasticity deformation effect amount, the program are independently controlled for different incoming fast pressing test data extrapolation methods to stagnation temperature stagnation pressure
The Dependence Problem of wind tunnel test capacity of equipment processed, the independent change stagnation pressure wind tunnel test side that can be realized using most wind-tunnel
Method, the wind tunnel test data that different Reynolds number combines with incoming ram compression are obtained, difficulty, the preparatory period of wind tunnel test is greatly reduced
And cost, dependence of the model static elasticity deformation effect amendment to wind-tunnel is eliminated, carries out corresponding amendment examination for all kinds of conventional wind-tunnel
Offer technical support is provided.
This programme is achieved by the following technical measures：
A kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount, includes following steps：
A, first according to the Parameter Conditions of wind tunnel test, it is determined that carrying out the separation wind tunnel test of aeroelastic effect deformation effect amount
Reynolds number Re combined with incoming ram compression q, the number of combination should be more than or equal to 3；
B, under reynolds number Re and incoming ram compression q combination parameters, analyzed using the mode of finite element or ground load test
Whether stress or deformation of the wing structure under the effect of corresponding aerodynamic loading meet the strength condition of structure, if be unsatisfactory for, from
It is new to return to step a, the combination parameter of amendment reynolds number Re and incoming ram compression q, if it is satisfied, continuing step c；
C, according to reynolds number Re and incoming ram compression q combination parameter, using wind-tunnel parameter table, calculate and determine wind-tunnel fortune
Capable stagnation pressure control parameter P0；
D, stagnation pressure control parameter P is analyzed0Whether stagnation pressure range of operation that wind-tunnel allow is located at, if the stagnation pressure beyond permission
Scope, step a is returned to, further correct the combination parameter of reynolds number Re and incoming ram compression q, if meeting that stagnation pressure runs model
Enclose, then into step e；
E, according to the wind tunnel operation stagnation pressure control parameter P determined in step c and step d0, drive wind tunnel operation and start to try
Test, the elastic profile aerodynamic coefficient data under at least 3 groups of different parameters combinations (ξ, λ) are obtained by wind-tunnel balance measurement
Cf,elastic；
F, the elastic profile aerodynamic coefficient data C under 3 groups of different (ξ, λ) parameter combinations is utilizedf,elastic, build undetermined
Coefficient k1、k2、k3System of linear equations, then solve system of linear equations, obtain coefficient k2：
A=ξ1(λ2-λ3)+ξ2(λ3-λ1)+ξ3(λ1-λ2)；
G, usage factor k2, then in conjunction with parameter lambda, gas caused by the aeroelastic effect deformation under corresponding states can be obtained
Coefficient of impact variation delta Cf,elastic
ΔCf,elastic(λ)=k2λ。
As the preferred of this programme：In step a, the ratio between reynolds number Re or incoming ram compression q maxima and minima
Value is more than 2.0.
Compared with existing wind tunnel model aeroelastic effect deformation effect investigative technique, different parameters group proposed by the present invention
The technological process of wind tunnel test Data Acquisition Model static elasticity deformation effect amount, achieves following effect corresponding to conjunction：
Only aeroelastic effect deformation can be achieved to aerodynamic coefficient influence amount by becoming stagnation pressure wind tunnel test in the present invention
Separation, the experiment of wind tunnel model aeroelastic effect deformation effect is reduced to the dependence of wind-tunnel facilities ability, the technological process energy
Enough it is applied to vast majority of conventional test air tunnel, in the case of the independent change ram compression wind tunnel test equipment not having in current China,
A kind of feasible technological means is provided for the research of model aeroelastic effect deformation effect, China's wind tunnel test will be effectively improved
The precision of data correction, the test data support of more high accurancy and precision is provided for the design of aerospace flight vehicle.
The present invention is the aeroelastic effect deformation effect amount in wind tunnel test data that can be achieved only by routine test wind-tunnel
Separation, reduces difficulty and the preparatory period of this kind of wind tunnel test, the efficiency of experiment greatly improved.
Aerodynamic coefficient data of the present invention based on different parameters combination, can go out model using algebraic method with quick separating
Aeroelastic effect deforms the influence amount to aerodynamic coefficient, is easy to analyze aeroelastic effect deformation in real time to aerodynamic coefficient
Influence, be that the wind tunnel data of testing ground is analyzed so as to find problem present in wind tunnel test data much sooner
With the analysis tool of assessment offer rapidly and efficiently, it can effectively avoid experiment train number caused by test data error analysis from scrapping and ask
Topic, the success rate of experiment is improved, reduce cycle and the cost of experiment.
As can be seen here, the present invention compared with prior art, has substantive distinguishing features and progress, its beneficial effect implemented
It is obvious.
Brief description of the drawings
Fig. 1 is the structural representation of the specific embodiment of the invention.
Embodiment
For the technical characterstic for illustrating this programme can be understood, below by an embodiment, and its accompanying drawing is combined, it is right
This programme is illustrated.
In wind tunnel test, other parameters (such as Mach number Ma, Model angle of attack α) change is not considered, the gas under elastic profile
Coefficient of impact Cf,elasticReynolds number Re and incoming ram compression q function can be expressed as
Cf,elastic=f (Re, q) (1)
The presence of incoming ram compression can cause the static elasticity of wind tunnel model wing structure to deform, therefore can be by aerodynamic coefficient
It is divided into rigid profile aerodynamic coefficient Cf,rigidCause aerodynamic coefficient variation delta C with the deformation of wing aeroelastic effectf,elastic
Two parts, wherein Cf,rigidOnly change with Re, Δ Cf,elasticChange with Re and q, can be expressed as with formula：
Cf,elastic(Re, q)=Cf,rigid(Re)+ΔCf,elastic(Re,q) (2)
The deformation of wind tunnel model static elasticity is normally in the range of the linear small deformation of structure, can not had to before and after considering to deform
Influence of the aerodynamic loading changes in distribution to malformation, therefore, aerodynamic coefficient variation delta caused by static elasticity deformation
Cf,elasticIt is proportional to the Structural Static deflection of wing.And Structural Static deflection is proportional to aerodynamic loading that wing structure is subject to, anti-
Than in the elastic modulus E of structural material, and aerodynamic loading is proportional to wind-tunnel incoming ram compression q, therefore may infer that Δ Cf,elasticWith
Linear ratio relation is shown as between load factor q/E.And when load factor q/E is zero, incoming ram compression q is zero, wing knot
Structure is not acted on by aerodynamic loading, and wing static elasticity is deformed into zero, therefore Δ Cf,elasticIt is also equal to zero.
On the other hand, reynolds number Re has certain influence on lift coefficient, but influence amount is high with respect to lift coefficient absolute magnitude
Rank is a small amount of, and the influence for the quiet deformation of wing structure that the change of reynolds number Re is dominated to lift load is very small, i.e. reynolds number Re pair
ΔCf,elasticInfluence can be ignored, therefore have
ΔCf,elastic(λ)=k2λ (3)
In formula, λ is intermediate parameters and λ=107× q/E, k2For coefficient to be determined, machine caused by aerodynamic loading is characterized
Wing aeroelastic effect is deformed to aerodynamic coefficient CfInfluence degree, as long as coefficient k is determined2, you can according to during wind tunnel operation
Aerodynamic coefficient variation delta C caused by static elasticity deformation is calculated in load factor q/Ef,elastic。
Formula (3) substitutes into formula (2), can obtain
Cf,elastic(Re, λ)=Cf,Rigid(Re)+k2λ (4)
Coefficient k can not directly be determined by formula (4)2, we introduce Cf,rigidFunction change between reynolds number Re is closed
System, number of parameters is reduced, so as to determine parameter k by Solving Linear2.Numerous results of study show, rigid profile gas
Coefficient of impact Cf,rigidApproximately linear variation relation is shown as between the logarithm lg (Re) of Reynolds number, therefore is had
Cf,Rigid(ξ)=k1ξ+k3 (5)
In formula, ξ is intermediate parameters and ξ=lg (Re/Re0), Re0=106, k1、k3For coefficient to be determined.By formula (5) generation
Enter formula (4), can obtain
Cf,elastic(ξ, λ)=k1ξ+k2λ+k3 (6)
Formula (6) has 3 undetermined coefficient k1、k2、k3, it is only necessary to the data of 3 groups of different (ξ, λ) combinations can be built on being
Number k1、k2、k3System of linear equations, it is as follows.
Solve system of linear equations, you can obtain coefficient k1、k2、k3,
So as to the coefficient k determined according to formula (8)2, the deformation pair of model wing aeroelastic effect is calculated using formula (3)
The influence amount Δ C of aerodynamic coefficientf,elastic。
Based on above-mentioned measuring method, the wind tunnel test of given aircraft model, acquisition pneumostatic proposed by the present invention are directed to
The method of dynamic elasticity deformation effect amount is：
A kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount, includes following steps：
A, first according to the Parameter Conditions of wind tunnel test, it is determined that carrying out the separation wind tunnel test of aeroelastic effect deformation effect amount
Reynolds number Re combined with incoming ram compression q, the number of combination should be more than or equal to 3；
B, under reynolds number Re and incoming ram compression q combination parameters, analyzed using the mode of finite element or ground load test
Whether stress or deformation of the wing structure under the effect of corresponding aerodynamic loading meet the strength condition of structure, if be unsatisfactory for, from
It is new to return to step a, the combination parameter of amendment reynolds number Re and incoming ram compression q, if it is satisfied, continuing step c；
C, according to reynolds number Re and incoming ram compression q combination parameter, using wind-tunnel parameter table, calculate and determine wind-tunnel fortune
Capable stagnation pressure control parameter P0；
D, stagnation pressure control parameter P is analyzed0Whether stagnation pressure range of operation that wind-tunnel allow is located at, if the stagnation pressure beyond permission
Scope, step a is returned to, further correct the combination parameter of reynolds number Re and incoming ram compression q, if meeting that stagnation pressure runs model
Enclose, then into step e；
E, according to the wind tunnel operation stagnation pressure control parameter P determined in step c and step d0, drive wind tunnel operation and start to try
Test, the elastic profile aerodynamic coefficient data under at least 3 groups of different parameters combinations (ξ, λ) are obtained by wind-tunnel balance measurement
Cf,elastic；
F, the elastic profile aerodynamic coefficient data C under 3 groups of different (ξ, λ) parameter combinations is utilizedf,elastic, build undetermined
Coefficient k1、k2、k3System of linear equations, then solve system of linear equations, obtain coefficient k2：
A=ξ1(λ2-λ3)+ξ2(λ3-λ1)+ξ3(λ1-λ2)；
G, usage factor k2, then in conjunction with parameter lambda, gas caused by the aeroelastic effect deformation under corresponding states can be obtained
Coefficient of impact variation delta Cf,elastic
ΔCf,elastic(λ)=k2λ。
In step a, the ratio between reynolds number Re or incoming ram compression q maxima and minima is more than 2.0.
Only aeroelastic effect deformation can be achieved to aerodynamic coefficient influence amount by becoming stagnation pressure wind tunnel test in the present invention
Separation, the experiment of wind tunnel model aeroelastic effect deformation effect is reduced to the dependence of wind-tunnel facilities ability, the technological process energy
Enough it is applied to vast majority of conventional test air tunnel, in the case of the independent change ram compression wind tunnel test equipment not having in current China,
A kind of feasible technological means is provided for the research of model aeroelastic effect deformation effect, China's wind tunnel test will be effectively improved
The precision of data correction, the test data support of more high accurancy and precision is provided for the design of aerospace flight vehicle.
The present invention is the aeroelastic effect deformation effect amount in wind tunnel test data that can be achieved only by routine test wind-tunnel
Separation, reduces difficulty and the preparatory period of this kind of wind tunnel test, the efficiency of experiment greatly improved.
Aerodynamic coefficient data of the present invention based on different parameters combination, can go out model using algebraic method with quick separating
Aeroelastic effect deforms the influence amount to aerodynamic coefficient, is easy to analyze aeroelastic effect deformation in real time to aerodynamic coefficient
Influence, be that the wind tunnel data of testing ground is analyzed so as to find problem present in wind tunnel test data much sooner
With the analysis tool of assessment offer rapidly and efficiently, it can effectively avoid experiment train number caused by test data error analysis from scrapping and ask
Topic, the success rate of experiment is improved, reduce cycle and the cost of experiment.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
All any modification, equivalent and improvement made within refreshing and principle etc., should be included in the scope of the protection.
Claims (2)
1. a kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount, it is characterized in that：Comprise the following steps：
A, first according to the Parameter Conditions of wind tunnel test, it is determined that carrying out the thunder of aeroelastic effect deformation effect amount separation wind tunnel test
Promise number Re combines with incoming ram compression q, and the number of combination should be more than or equal to 3；
B, under reynolds number Re and incoming ram compression q combination parameters, wing is analyzed using the mode of finite element or ground load test
Whether stress or deformation of the structure under the effect of corresponding aerodynamic loading meet the strength condition of structure, if be unsatisfactory for, are returned from newly
Return to step a, the combination parameter of amendment reynolds number Re and incoming ram compression q, if it is satisfied, continuing step c；
C, according to reynolds number Re and incoming ram compression q combination parameter, using wind-tunnel parameter table, calculate and determine wind tunnel operation
Stagnation pressure control parameter P0；
D, stagnation pressure control parameter P is analyzed0Whether the stagnation pressure range of operation allowed positioned at wind-tunnel, if beyond the stagnation pressure scope of permission,
Step a is returned to, the combination parameter of reynolds number Re and incoming ram compression q is further corrected, if meeting stagnation pressure range of operation, enters
Enter step e；
E, according to the wind tunnel operation stagnation pressure control parameter P determined in step c and step d0, drive wind tunnel operation and start to test, lead to
The elastic profile aerodynamic coefficient data C crossed under wind-tunnel balance measurement acquisition at least 3 groups of different parameters combinations (ξ, λ)f,elastic；
F, the elastic profile aerodynamic coefficient data C under 3 groups of different (ξ, λ) parameter combinations is utilizedf,elastic, build undetermined coefficient
k1、k2、k3System of linear equations, then solve system of linear equations, obtain coefficient k2；
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</mtd>
</mtr>
</mtable>
</mfenced>
</mrow>
A=ξ1(λ2-λ3)+ξ2(λ3-λ1)+ξ3(λ1-λ2)；
G, usage factor k2, then in conjunction with parameter lambda, aerodynamic force caused by the aeroelastic effect deformation under corresponding states can be obtained
Index variation amount Δ Cf,elastic
ΔCf,elastic(λ)=k2λ。
2. a kind of method for obtaining wind tunnel model aeroelastic effect deformation effect amount according to claim 1, it is characterized in that：
In the step a, the ratio between reynolds number Re or incoming ram compression q maxima and minima is more than 2.0.
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