CN105335549A - Upper and lower airfoil deformation superposition method - Google Patents
Upper and lower airfoil deformation superposition method Download PDFInfo
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- CN105335549A CN105335549A CN201510621284.0A CN201510621284A CN105335549A CN 105335549 A CN105335549 A CN 105335549A CN 201510621284 A CN201510621284 A CN 201510621284A CN 105335549 A CN105335549 A CN 105335549A
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Abstract
The invention provides an upper and lower airfoil deformation superposition method. The method comprises the following steps: determining and obtaining flexibility matrixes in the centers of aerodynamic grid units of upper and lower airfoils; with a flexibility method, decomposing airfoil structure deformation into superposition of deformations generated under the single action of aerodynamic loads of the upper airfoil and the lower airfoil, and obtaining airfoil structure deformation amounts under the single action of the aerodynamic loads of the upper airfoil and the lower airfoil; according to initial static grid coordinates of the airfoils, obtaining deformation interpolation matrixes between the upper airfoil and the lower airfoil with a surface spline method, wherein the deformation interpolation matrixes between the upper airfoil and the lower airfoil include a deformation interpolation matrix [TUL] from the grid center of the upper airfoil to the grid center of the lower airfoil, an interpolation matrix [TLL] from the grid center of the lower airfoil to grid points of the lower airfoil, and an interpolation matrix [TLU] from the grid center of the lower airfoil to grid points of the upper airfoil; and according to the airfoil structure deformation amounts under the single action of the aerodynamic loads of the upper airfoil and the lower airfoil, and the deformation interpolation matrixes of the upper airfoil and the lower airfoil, determining upper and lower airfoil deformation superposition. According to the method, flexibility method based static aeroelastic CFD/CSD coupling calculation is suitable for any airfoil grid distribution situation.
Description
Technical field
The present invention relates to a kind of method of Fluid Mechanics Computation field, specifically relate to a kind of upper lower aerofoil deformational overprint method.
Background technology
Aeroelasticity is a cross discipline of research aerodynamic force, elastic force and inertial force interphase interaction.Eighties of last century beginning of the nineties, start both at home and abroad to be devoted to be coupled iterative calculation method research based on the aeroelasticity CFD/CSD of Euler/N-S equation.At present, CFD/CSD coupling calculates and is comparatively widely used in engineering reality, but also there are some technological difficulties and ins and outs have to be solved.Aeroelastic effect problem ignores the impact of inertial force, and its CFD/CSD is coupled to calculate and adopts Unsteady Flow and malformation alternating iteration to calculate until the method for convergence, and the quiet distortion of aerofoil then adopts flexibility method to calculate usually.
The fluid domain that tradition fluid-wall interaction calculates and solid domain adopt different grid system respectively, carry out information transmission, all need to carry out interface information transmission at each iteration step by fluid-wall interaction interface information Transfer Technology.After Flexibility Matrix is interpolated into aerofoil aerodynamic grid point from system point, carries out aeroelastic effect CFD/CSD coupling based on single aerodynamic grid system and calculate, fluid-wall interaction interface information transmission link repeatedly can be avoided, effectively improve counting yield.According to flexibility method, the malformation Flexibility Matrix equaled in aerodynamic grid system at aerofoil aerodynamic grid cell heart place is multiplied by the force vector of corresponding upper lower aerofoil unit aerodynamic force composition, therefore require that the aerodynamic grid of upper lower aerofoil overlaps at projection plane, in practical application for asymmetric aerofoil be difficult to realize, add aerofoil grid distribution difficulty and limit aeroelastic effect CFD/CSD be coupled calculate application.
Summary of the invention
For overcoming above-mentioned the deficiencies in the prior art, the present invention is directed to the limitation that on traditional flexibility method aeroelastic effect calculation requirement, lower aerofoil aerodynamic grid overlaps at projection plane, a kind of upper lower aerofoil deformational overprint method is provided, makes the aeroelastic effect CFD/CSD coupling calculating based on flexibility method be applicable to any aerofoil grid distribution situation.
Realizing the solution that above-mentioned purpose adopts is:
Lower aerofoil deformational overprint method in one, its improvements are: said method comprising the steps of:
Determine to obtain lower aerofoil aerodynamic grid cell heart place Flexibility Matrix;
Use flexibility method, by the superposition of deflection of airfoil structure Deformation partition for producing under top airfoil and lower aerofoil aerodynamic loading independent role, the airfoil structure deflection in acquisition under lower aerofoil aerodynamic loading independent role;
According to aerofoil initial static mesh coordinate, adopt face spline method to obtain between upper lower aerofoil and be out of shape interpolating matrix, comprising: the top airfoil lattice heart is to the deflection interpolating matrix [T of the lower aerofoil lattice heart
uL], the lower aerofoil lattice heart is to the interpolating matrix [T of lower aerofoil lattice point
lL] and the lower aerofoil lattice heart to top airfoil lattice point volume interpolating matrix [T
lU];
According to the airfoil structure deflection under upper lower aerofoil aerodynamic loading independent role and upper lower aerofoil distortion interpolating matrix, determine described upper lower aerofoil deformational overprint.
Preferably, described step: determine described upper lower aerofoil aerodynamic grid cell heart place's flexibility cushion value, comprising:
Structure analysis is used to obtain the Flexibility Matrix at system point place;
Employing face spline method, is interpolated into upper lower aerofoil aerodynamic grid cell heart place respectively by system point place Flexibility Matrix, obtain top airfoil aerodynamic grid cell heart place Flexibility Matrix [C
aU] and lower aerofoil aerodynamic grid cell heart place Flexibility Matrix [C
aL].
Preferably, described step: use flexibility method, by the superposition of deflection of airfoil structure Deformation partition for producing under top airfoil and lower aerofoil aerodynamic loading independent role, obtains the airfoil structure deflection calculated under upper lower aerofoil aerodynamic loading independent role; Comprise:
S201, utilization CFD obtain top airfoil grid cell aerodynamic loading { F
uand lower aerofoil grid cell aerodynamic loading { F
l;
S202, according to upper lower aerofoil aerodynamic grid cell heart place Flexibility Matrix, calculate the lower aerofoil aerodynamic grid lattice heart place deflection [C under the effect of lower aerofoil aerodynamic loading respectively
aL] { F
land the effect of independent top airfoil aerodynamic loading under top airfoil deflection [C
aU] { F
u.
S203, according to flexibility method, determine that the malformation amount at aerofoil aerodynamic grid cell heart place is: { Δ z}=[C
a] { B}=[C
a] { F
l+ F
u}=[C
aL] { F
l}+[C
aU] { F
u;
Wherein, [C
a] be the Flexibility Matrix at aerodynamic grid cell heart place, { B} is the aerodynamic force vector of the corresponding grid cell of upper lower aerofoil, and L, U represent upper and lower aerofoil respectively, and F is the aerofoil grid cell aerodynamic loading that CFD calculates, [C
aL] { F
lbe the distortion at only lower aerofoil grid cell lattice heart place under the effect of lower aerofoil aerodynamic loading, [C
aU] { F
uit is the distortion at only top airfoil aerodynamic grid cell heart place under the effect of top airfoil aerodynamic loading.
Preferably, described step: determine described upper lower aerofoil deformational overprint, comprising:
S401, by the top airfoil cell heart place distortion [C
aU] { F
uinterpolation is to lower aerofoil [T
uL] [C
aU] { F
u, and be out of shape [C with lower aerofoil cell heart place
aL] { F
lsuperpose, obtain lower aerofoil cell heart place's true strain [C
aL] { F
l}+[T
uL] [C
aU] { F
u;
S402, the place's true strain of the lower aerofoil cell heart is interpolated into lower aerofoil lattice point place, obtains lower aerofoil lattice point true strain [Δ z
l]=[T
lL] ([C
aL] { F
l}+[T
uL] [C
aU] { F
u);
S403, the place's true strain of the lower aerofoil cell heart is interpolated into interpolation to top airfoil lattice point place, obtains top airfoil lattice point place's true strain [Δ z
u]=[T
lU] ([C
aL] { F
l}+[T
uL] [C
aU] { F
u);
Wherein, [C
a] be the Flexibility Matrix at aerodynamic grid cell heart place, { B} is the aerodynamic force vector of the corresponding grid cell of upper lower aerofoil, and subscript L, U represent upper and lower aerofoil respectively, and F represents the aerofoil grid cell aerodynamic loading that CFD calculates, [C
aL] { F
lbe the distortion at only lower aerofoil grid cell lattice heart place under the effect of lower aerofoil aerodynamic loading, [C
aU] { F
uit is the distortion at only top airfoil aerodynamic grid cell heart place under the effect of top airfoil aerodynamic loading.
Compared with immediate prior art, the present invention has following beneficial effect:
Method provided by the invention considers that upper lower aerofoil aerodynamic grid does not overlap situation on a projection plane, could superpose upper lower aerofoil aerodynamic loading independent role lower aerofoil distortion after mutual interpolation between upper lower aerofoil; Breach the limitation that on traditional flexibility method aeroelastic effect calculation requirement, lower aerofoil aerodynamic grid overlaps at projection plane, under being applicable to any aerofoil grid distribution situation, aeroelastic effect CFD/CSD coupling calculates, and effectively improves range of application.
Accompanying drawing explanation
Fig. 1 is wing centre section facial disfigurement superimposing technique calculation flow chart of the present invention;
Fig. 2 is aerofoil surface grid chart in the present embodiment;
Fig. 3 is the present embodiment projection plane wing structure point distribution plan;
Fig. 4 is the present embodiment projection plane aerofoil aerodynamic grid point distribution plan;
Fig. 5 is the present embodiment wing flexibility method aeroelastic effect CFD/CSD coupling result of calculation schematic diagram.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described in further detail.
Below with reference to accompanying drawings exemplary embodiment of the present disclosure is described in more detail.Although show exemplary embodiment of the present disclosure in accompanying drawing, but be to be understood that, can realize in a variety of manners the disclosure and not should limit by the embodiment set forth here, other embodiments can comprise structure, logic, electric, process and other change.Embodiment only represents possible change.On the contrary, provide these embodiments to be in order to more thoroughly the disclosure can be understood, and complete for the scope of the present disclosure can be conveyed to those skilled in the art.Herein, these embodiments of the present invention can be represented with term " invention " individually or always, this is only used to conveniently, and if in fact disclose the invention more than, be not the scope that will limit this application is automatically any single invention or inventive concept.
As shown in Figure 1, Fig. 1 is aerofoil deformational overprint technique computes process flow diagram of the present invention; When the present invention is directed to traditional flexibility method aeroelastic effect CFD/CSD coupling calculating, the limitation that in requirement, lower aerofoil aerodynamic grid overlaps at projection plane, a kind of method of upper lower aerofoil deformational overprint is provided, makes the aeroelastic effect CFD/CSD coupling calculating based on flexibility method be applicable to any aerofoil grid distribution situation.
The method comprises the following steps:
Determine to obtain lower aerofoil aerodynamic grid cell heart place Flexibility Matrix.
Airfoil structure deflection in calculating under lower aerofoil aerodynamic loading independent role.
Deflection interpolating matrix between lower aerofoil in calculating.
Aerofoil true strain superposition calculation.
For step: determine to obtain upper lower aerofoil aerodynamic grid cell heart place Flexibility Matrix.
Aeroelastic effect CFD/CSD coupling based on single aerodynamic grid system calculates the Flexibility Matrix needing aerofoil aerodynamic grid cell heart place.In the present embodiment, use structure analysis to obtain the Flexibility Matrix at system point place, obtain a kind of embodiment distribution plan of projection plane (XOY) top wing system point as shown in Figure 3.
The present invention adopts face spline method, system point place Flexibility Matrix is interpolated into respectively upper lower aerofoil aerodynamic grid cell heart place, obtains top airfoil aerodynamic grid cell heart place Flexibility Matrix [C
aU], lower aerofoil aerodynamic grid cell heart place Flexibility Matrix [C
aL].
Flexibility Matrix interpolation is only relevant to aerofoil initial static grid, after pre-treatment has calculated, directly uses in aeroelastic effect CFD/CSD coupling iterative process.
For step: the airfoil structure deflection in calculating under lower aerofoil aerodynamic loading independent role.
The present invention uses flexibility method, by the superposition of deflection of airfoil structure Deformation partition for producing under top airfoil and lower aerofoil aerodynamic loading independent role, and the airfoil structure deflection in acquisition under lower aerofoil aerodynamic loading independent role.Concrete grammar is:
S201, CFD calculate top airfoil grid cell aerodynamic loading { F
u, lower aerofoil grid cell aerodynamic loading { F
l;
Lower aerofoil Flexibility Matrix in S202, utilization, calculates the lower aerofoil aerodynamic grid lattice heart place deflection [C under the effect of lower aerofoil aerodynamic loading respectively
aL] { F
land the effect of independent top airfoil aerodynamic loading under top airfoil deflection [C
aU] { F
u.
S203, according to flexibility method, determine that the malformation amount at aerofoil aerodynamic grid cell heart place is: { Δ z}=[C
a] { B}=[C
a] { F
l+ F
u}=[C
aL] { F
l}+[C
aU] { F
u;
Wherein, [C
a] be the Flexibility Matrix at aerodynamic grid cell heart place, { B} is the aerodynamic force vector of the corresponding grid cell of upper lower aerofoil, and subscript L, U represent upper and lower aerofoil respectively, and F represents the aerofoil grid cell aerodynamic loading that CFD calculates, [C
aL] { F
lthe distortion at only lower aerofoil grid cell lattice heart place under the effect of lower aerofoil aerodynamic loading, [C
aU] { F
uit is the distortion at only top airfoil aerodynamic grid cell heart place under the effect of top airfoil aerodynamic loading.
For step: deflection interpolating matrix between lower aerofoil in calculating.
As shown in Figure 4, upper lower aerofoil aerodynamic grid does not overlap at projection plane, and in figure, quadrilateral represents lower aerofoil aerodynamic grid point, and triangle represents top airfoil aerodynamic grid point.
In consideration, lower aerofoil aerodynamic grid does not overlap situation on a projection plane, will be out of shape [C
aL] { F
l, [C
aU] { F
ucould superpose after mutual interpolation between upper lower aerofoil.Meanwhile, be that grid cell lattice point is out of shape in CFD/CSD coupling computation process, the distortion of lattice heart place is interpolated into lattice point place.
In calculating, between lower aerofoil, the method for deflection interpolating matrix is: according to aerofoil initial static mesh coordinate, adopts face spline method to calculate between lower aerofoil and is out of shape interpolating matrix, comprising:
The top airfoil lattice heart is to the deflection interpolating matrix [T of the lower aerofoil lattice heart
uL];
The lower aerofoil lattice heart is to the interpolating matrix [T of lower aerofoil lattice point
lL]; And
The lower aerofoil lattice heart is to top airfoil lattice point volume interpolating matrix [T
lU].
Between upper lower aerofoil, deflection interpolating matrix is only relevant to aerofoil initial static grid, after pre-treatment has calculated three interpolating matrixs, directly uses in aeroelastic effect CFD/CSD coupling iterative process.
For step: upper bottom wing; Carry out aeroelastic effect CFD/CSD coupling after facial disfigurement superposition calculation to calculate.
Be the superposition { Δ z}=[C of deflection under the independent aerodynamic loading effect of upper lower aerofoil by aerofoil Deformation partition
aL] { F
l}+[C
aU] { F
u, in conjunction with upper lower aerofoil distortion interpolating matrix, the true strain of superposition calculation aerofoil aerodynamic grid point.
First, by top airfoil cell heart place distortion [C
aU] { F
uinterpolation is to lower aerofoil [T
uL] [C
aU[{ F
u, and be out of shape [C with lower aerofoil cell heart place
aL] { F
lsuperpose, obtain lower aerofoil cell heart place's true strain [C
aL] { F
l}+[T
uL] [C
aU] { F
u;
Then, the place's true strain of the lower aerofoil cell heart is interpolated into lower aerofoil lattice point place, obtains lower aerofoil lattice point true strain [Δ z
l]=[T
lL] ([C
aL] { F
l}+[T
uL] [C
aU] { F
u);
Finally, the place's true strain of the lower aerofoil cell heart is interpolated into top airfoil lattice point place, obtains top airfoil lattice point place's true strain [Δ z
u]=[T
lU] ([C
aL] { F
l}+[T
uL] [C
aU] { F
u);
Namely the upper lower aerofoil aerodynamic grid lattice point place distortion obtained is expressed as follows respectively:
{Δz
L}＝[T
LL]([C
AL]{F
L}+[T
UL]([C
AU]{F
U}))
{Δz
U}＝[T
LU]([C
AL]{F
L}+[T
UL]([C
AU]{F
U}))
Be coupled for aeroelastic effect CFD/CSD after aerofoil distortion calculating completes and calculate, Fig. 5 gives this wing aeroelastic effect result of calculation.
Finally should be noted that: above embodiment is only for illustration of the technical scheme of the application but not the restriction to its protection domain; although with reference to above-described embodiment to present application has been detailed description; those of ordinary skill in the field are to be understood that: those skilled in the art still can carry out all changes, amendment or equivalent replacement to the embodiment of application after reading the application; but these change, revise or be equal to replacement, all applying within the claims awaited the reply.
Claims (4)
1. a upper lower aerofoil deformational overprint method, is characterized in that: said method comprising the steps of:
Determine to obtain lower aerofoil aerodynamic grid cell heart place Flexibility Matrix;
Use flexibility method, by the superposition of deflection of airfoil structure Deformation partition for producing under top airfoil and lower aerofoil aerodynamic loading independent role, the airfoil structure deflection in acquisition under lower aerofoil aerodynamic loading independent role;
According to aerofoil initial static mesh coordinate, adopt face spline method to obtain between upper lower aerofoil and be out of shape interpolating matrix, comprising: the top airfoil lattice heart is to the deflection interpolating matrix [T of the lower aerofoil lattice heart
uL], the lower aerofoil lattice heart is to the interpolating matrix [T of lower aerofoil lattice point
lL] and the lower aerofoil lattice heart to top airfoil lattice point volume interpolating matrix [T
lU];
According to the airfoil structure deflection under upper lower aerofoil aerodynamic loading independent role and upper lower aerofoil distortion interpolating matrix, determine described upper lower aerofoil deformational overprint.
2. a kind of upper lower aerofoil deformational overprint method as claimed in claim 1, is characterized in that: described step: determine described upper lower aerofoil aerodynamic grid cell heart place's flexibility cushion value, comprising:
Structure analysis is used to obtain the Flexibility Matrix at system point place;
Employing face spline method, is interpolated into upper lower aerofoil aerodynamic grid cell heart place respectively by system point place Flexibility Matrix, obtain top airfoil aerodynamic grid cell heart place Flexibility Matrix [C
aU] and lower aerofoil aerodynamic grid cell heart place Flexibility Matrix [C
aL].
3. a kind of upper lower aerofoil deformational overprint method as claimed in claim 1, it is characterized in that: described step: use flexibility method, by the superposition of deflection of airfoil structure Deformation partition for producing under top airfoil and lower aerofoil aerodynamic loading independent role, obtain the airfoil structure deflection calculated under upper lower aerofoil aerodynamic loading independent role; Comprise:
S201, utilization CFD obtain top airfoil grid cell aerodynamic loading { F
uand lower aerofoil grid cell aerodynamic loading { F
l;
S202, according to upper lower aerofoil aerodynamic grid cell heart place Flexibility Matrix, calculate the lower aerofoil aerodynamic grid lattice heart place deflection [C under the effect of lower aerofoil aerodynamic loading respectively
aL] { F
land the effect of independent top airfoil aerodynamic loading under top airfoil deflection [C
aU] { F
u.
S203, according to flexibility method, determine that the malformation amount at aerofoil aerodynamic grid cell heart place is: { Δ z}=[C
a] { B}=[C
a] { F
l+ F
u}=[C
aL] { F
l}+[C
aU] { F
u;
Wherein, [C
a] be the Flexibility Matrix at aerodynamic grid cell heart place, { B} is the aerodynamic force vector of the corresponding grid cell of upper lower aerofoil, and L, U represent upper and lower aerofoil respectively, and F is the aerofoil grid cell aerodynamic loading that CFD calculates, [C
aL] { F
lbe the distortion at only lower aerofoil grid cell lattice heart place under the effect of lower aerofoil aerodynamic loading, [C
aU] { F
uit is the distortion at only top airfoil aerodynamic grid cell heart place under the effect of top airfoil aerodynamic loading.
4. a kind of upper lower aerofoil deformational overprint method as claimed in claim 1, is characterized in that: described step: determine described upper lower aerofoil deformational overprint, comprising:
S401, by the top airfoil cell heart place distortion [C
aU] { F
uinterpolation is to lower aerofoil [T
uL] [C
aU] { F
u, and be out of shape [C with lower aerofoil cell heart place
aL] { F
lsuperpose, obtain lower aerofoil cell heart place's true strain [C
aL] { F
l}+[T
uL] [C
aU] { F
u;
S402, the place's true strain of the lower aerofoil cell heart is interpolated into lower aerofoil lattice point place, obtains lower aerofoil lattice point true strain [Δ z
l]=[T
lL] ([C
aL] { F
l}+[T
uL] [C
aU] { F
u);
S403, the place's true strain of the lower aerofoil cell heart is interpolated into interpolation to top airfoil lattice point place, obtains top airfoil lattice point place's true strain [Δ z
u]=[T
lU] ([C
aL] { F
l}+[T
uL] [C
aU] { F
u);
Wherein, [C
a] be the Flexibility Matrix at aerodynamic grid cell heart place, { B} is the aerodynamic force vector of the corresponding grid cell of upper lower aerofoil, and subscript L, U represent upper and lower aerofoil respectively, and F represents the aerofoil grid cell aerodynamic loading that CFD calculates, [C
aL] { F
lbe the distortion at only lower aerofoil grid cell lattice heart place under the effect of lower aerofoil aerodynamic loading, [C
aU] { F
uit is the distortion at only top airfoil aerodynamic grid cell heart place under the effect of top airfoil aerodynamic loading.
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| CN106599486A (en) * | 2016-12-16 | 2017-04-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for establishing aircraft wing deformable model |
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| CN108563885A (en) * | 2018-04-23 | 2018-09-21 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of flutter of aerofoil Model Beam rib layout rapid movement method and system |
| CN108563885B (en) * | 2018-04-23 | 2022-05-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and system for quickly moving wing flutter model beam rib layout |
| CN111581718A (en) * | 2020-04-13 | 2020-08-25 | 东南大学 | Time-varying spline interpolation method applied to wing vibration |
| CN112347561A (en) * | 2020-11-10 | 2021-02-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Static aeroelasticity analysis method, device, equipment and storage medium of aircraft |
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