CN110162823A - Consider the unsteady aerodynamic force calculation method of pneumatic face curved surface effect and normal direction movement - Google Patents
Consider the unsteady aerodynamic force calculation method of pneumatic face curved surface effect and normal direction movement Download PDFInfo
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Abstract
The present invention provides a kind of unsteady aerodynamic force calculation methods for considering pneumatic face curved surface effect and normal direction movement, this method comprises: carrying out grid dividing to face pneumatic after the deformation of aircraft；Obtain the structural elasticity mode of aircraft；It extracts structural elasticity mode relevant to face pneumatic after deformation and is interpolated on aerodynamic grid；Dipole elementary solution is arranged on grid, solves kernel function, and aerodynamic influence matrix is solved according to kernel function；Calculate the local normal vector of the aerodynamic grid in pneumatic face after deforming；Normal direction kinematical boundary condition is solved according to the normal direction mode in face pneumatic after deformation；Solve the unsteady aerodynamic force after deforming on pneumatic surface grids；The curved surface unsteady aerodynamic force of generalization is obtained according to the normal direction mode in the unsteady aerodynamic force on surface grids pneumatic after deformation and pneumatic face after deformation.It applies the technical scheme of the present invention, to solve the technical issues of cannot achieve accurate description and the calculating of flexible flier frequency domain unsteady aerodynamic force in the prior art.
Description
Technical field
The present invention relates to flight vehicle aerodynamic elasticity technical field more particularly to a kind of pneumatic face curved surface effects of consideration and normal direction
The unsteady aerodynamic force calculation method of movement.
Background technique
The calculating of unsteady aerodynamic force is the key link of Flight Vehicle Design and analysis, directly affects the motor-driven of aircraft
Property, flight stability and the assessment of safety.Therefore unsteady aerodynamic force calculating is aeroelasticity point in Flight Vehicle Design link
The pith of analysis, servo stabilization analysis, flight mechanics emulation, flying quality assessment, the reasonability and standard of Modeling Calculation
True property is to Flight Vehicle Design and analysis important in inhibiting.
With the raising of contemporary aircraft designing technique, the development of composite technology and the long endurance of aircraft high speed etc.
The growth requirement of aspect, flexible flier become the hot spot of recent aircraft research.Due to light weight, flexible big, flexibility flight
Under aerodynamic loading effect biggish flexible deformation can occur for device, and pneumatic face is also deformed into space curved surface therewith.Traditional, pneumatic bullet
Property the plate aerodynamics evaluation that generallys use of analysis cannot reflect that really pneumatic face shape is also unable to get accurately three-dimensional space
Flow field form, therefore the aerodynamic loading of flexible flier calculates and the curved surface effect in pneumatic face all must be taken into consideration.For unsteady
Calculating also needs the forms of motion to pneumatic face to analyze, and for flexible flier, is influenced by curved surface effect, it is non-fixed to cause
The effective exercise component of normal aerodynamic force is no longer confined to the Z component under plane configuration, but the moment is perpendicular to local pneumatic face structure
The normal direction component motion of type.When pneumatic face curved surface effect is significant, the otherness of Z-direction component motion and normal direction component motion is aobvious
It writes, if still carrying out the calculating of unsteady aerodynamic force using the Z component motion of plane configuration, necessarily causes large error, to rear
Continuous flutter analysis and pneumatic servo flexibility analysis affects.
Summary of the invention
The present invention provides a kind of unsteady aerodynamic force calculation method for considering pneumatic face curved surface effect and normal direction movement, energy
It is enough to solve the technical issues of cannot achieve accurate description and the calculating of flexible flier frequency domain unsteady aerodynamic force in the prior art.
It is non-the present invention provides a kind of unsteady aerodynamic force calculation method for considering pneumatic face curved surface effect and normal direction movement
Unsteady Flow calculation method include: after deformation to aircraft pneumatic face carry out grid dividing；It is dynamic that structure is carried out to aircraft
Mechanical analysis is to obtain the structural elasticity mode of aircraft；The pneumatic face after extracting and deforming in the structural elasticity mode of aircraft
Relevant structural elasticity mode is simultaneously interpolated into after deformation on the pneumatically aerodynamic grid in face；It is arranged on the grid in pneumatic face after deformation
Dipole elementary solution, solves the kernel function for considering pneumatic face deformation, solves aerodynamic influence matrix according to kernel function；It calculates
The local normal vector of the aerodynamic grid in pneumatic face after deformation；According to the structural elasticity mode in face pneumatic after deformation and local normal vector
The normal direction mode for solving pneumatic face after deforming solves normal direction kinematical boundary condition according to the normal direction mode in face pneumatic after deformation；Root
The unsteady aerodynamic force after deforming on pneumatic surface grids is solved according to normal direction kinematical boundary condition and aerodynamic influence matrix；Root
The curved surface of generalization is obtained according to the normal direction mode in the unsteady aerodynamic force on surface grids pneumatic after deformation and pneumatic face after deformation
Unsteady aerodynamic force.
Further, the kernel function for considering the deformation of pneumatic face isλ1=x-xj, wherein
(xi,yi,zi) it is receiving point coordinate, (xj,yj,zj) it is disturbance point coordinate,niIt is (xi,
yi,zi) at aerofoil normal direction, njIt is (xj,yj,zj) at aerofoil normal direction, ω be structural vibration circular frequency, U∞It is remote
Square speed of incoming flow, R' are the distance between receiving point and disturbance point, a∞For the velocity of sound of remote front incoming flow, M∞For free stream Mach number.
Further, after deformation pneumatic face normal direction mode f can according to the structural elasticity mode in face pneumatic after deformation with work as
Ground normal vector is multiplied to obtain.
Further, normal direction kinematical boundary condition isWherein, w is to wash speed under grid dimensionless normal direction
Degree, k are reduced frequency, and b is with reference to chord length, and f is the normal direction mode in pneumatic face after deformation, and n' is curved surface normal direction,For real part,For imaginary part.
Further, the unsteady aerodynamic force Δ c after deformation on pneumatic surface gridspIt can be according to w=D Δ cpIt obtains,
In, w is grid dimensionless normal direction downwash velocity, and D is aerodynamic influence matrix, Δ cpFor the unsteady pneumatic of aerodynamic grid
The column vector of power composition.
Further, aerodynamic influence matrix D can basisTo solve, wherein Δ
xjFor the middle length profile of j-th of grid, ljFor the length of the 1/4 string point of mistake of j-th of grid, χjFor 1/4 string sweepback of grid
Angle, KijFor kernel function.
Further, in step 1, for the tangential grid in pneumatic face at least more than 5, opening up can be according to net to grid after deformation
Lattice unit slenderness ratio is determined.
Further, the curved surface unsteady aerodynamic force of generalization can be according to unsteady pneumatic on surface grids pneumatic after deformation
Power is multiplied to obtain with the normal direction mode in face pneumatic after deformation.
It applies the technical scheme of the present invention, provides a kind of unsteady gas for considering pneumatic face curved surface effect and normal direction movement
The case where kinetic calculation method, this method is significantly deformed for this kind of pneumatic faces of flexible flier, introduce pneumatic face normal direction fortune
Dynamic calculation method, the accurate description unsteady effective exercise component in the pneumatic face of space curved surface and the meter for carrying out unsteady aerodynamic force
It calculates.This method compared with prior art, not only accurately describes curved surface aerodynamic characteristics from geometric aspects, also from kinematics angle
The accurate definition effective exercise component of unsteady aerodynamic force is spent, the accurate description and meter of frequency domain unsteady aerodynamic force are realized
It calculates.
Detailed description of the invention
Included attached drawing is used to provide to be further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together to illustrate the principle of the present invention with verbal description.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, be also possible to obtain other drawings based on these drawings.
Fig. 1 shows the non-of the considerations of providing according to a particular embodiment of the invention pneumatic face curved surface effect and normal direction movement
The flow diagram of Unsteady Flow calculation method；
Fig. 2 shows the schematic diagrames that the pneumatic surface grids of the three-dimension curved surface provided according to a particular embodiment of the invention divide；
Fig. 3 shows the dipole space layout schematic diagram provided according to a particular embodiment of the invention；
Fig. 4 show the dipole sub-line provided according to a particular embodiment of the invention, pressure spot and under wash a schematic diagram；
Fig. 5 shows the pneumatic face schematic diagram of the curved surface provided according to a particular embodiment of the invention；
Fig. 6 shows the V-f curve synoptic diagram of the FLUTTER CALCULATION result provided according to a particular embodiment of the invention；
Fig. 7 shows the V-g curve synoptic diagram of the FLUTTER CALCULATION result provided according to a particular embodiment of the invention.
Specific embodiment
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Ground description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is right below
The description only actually of at least one exemplary embodiment be it is illustrative, never as to the present invention and its application or use
Any restrictions.Based on the embodiments of the present invention, those of ordinary skill in the art are without creative efforts
Every other embodiment obtained, shall fall within the protection scope of the present invention.
It should be noted that term used herein above is merely to describe specific embodiment, and be not intended to restricted root
According to the illustrative embodiments of the application.As used herein, unless the context clearly indicates otherwise, otherwise singular
Also it is intended to include plural form, additionally, it should be understood that, when in the present specification using term "comprising" and/or " packet
Include " when, indicate existing characteristics, step, operation, device, component and/or their combination.
Unless specifically stated otherwise, positioned opposite, the digital table of the component and step that otherwise illustrate in these embodiments
It is not limited the scope of the invention up to formula and numerical value.Simultaneously, it should be appreciated that for ease of description, each portion shown in attached drawing
The size divided not is to draw according to actual proportionate relationship.For technology, side known to person of ordinary skill in the relevant
Method and equipment may be not discussed in detail, but in the appropriate case, and the technology, method and apparatus should be considered as authorizing explanation
A part of book.In shown here and discussion all examples, any occurrence should be construed as merely illustratively, and
Not by way of limitation.Therefore, the other examples of exemplary embodiment can have different values.It should also be noted that similar label
Similar terms are indicated in following attached drawing with letter, therefore, once it is defined in a certain Xiang Yi attached drawing, then subsequent attached
It does not need that it is further discussed in figure.
As shown in Figures 1 to 7, it provides according to a particular embodiment of the invention and a kind of considers pneumatic face curved surface effect and method
To the unsteady aerodynamic force calculation method of movement, which includes: pneumatic after deformation to aircraft
Face carries out grid dividing；Structural dynamical model is carried out to obtain the structural elasticity mode of aircraft to aircraft；From aircraft
Structural elasticity mode in extract structural elasticity mode relevant with face pneumatic after deformation and be interpolated into after deformation the pneumatically gas in face
On dynamic mesh；Dipole elementary solution is arranged on the grid in pneumatic face after deformation, solves the kernel function for considering pneumatic face deformation, root
Aerodynamic influence matrix is solved according to kernel function；Calculate the local normal vector of the aerodynamic grid in pneumatic face after deforming；According to change
The structural elasticity mode in pneumatic face and local normal vector solve the normal direction mode in pneumatic face after deformation after shape, according to pneumatic after deformation
The normal direction mode in face solves normal direction kinematical boundary condition；It is solved according to normal direction kinematical boundary condition and aerodynamic influence matrix
Unsteady aerodynamic force after deformation on pneumatic surface grids；According on surface grids pneumatic after deformation unsteady aerodynamic force and deformation after
The normal direction mode in pneumatic face is to obtain the curved surface unsteady aerodynamic force of generalization.
Using such configuration mode, a kind of unsteady aerodynamic force for considering pneumatic face curved surface effect and normal direction movement is provided
The case where calculation method, this method is significantly deformed for this kind of pneumatic faces of flexible flier, introduce pneumatic face normal direction movement meter
Calculation method, the unsteady effective exercise component in the pneumatic face of accurate description space curved surface and the calculating for carrying out unsteady aerodynamic force.It should
Method compared with prior art, not only accurately describes curved surface aerodynamic characteristics from geometric aspects, also quasi- from kinematics angle
The effective exercise component for really defining unsteady aerodynamic force, realizes accurate description and the calculating of frequency domain unsteady aerodynamic force.
Specifically, in the present invention, in order to complete the calculating of frequency domain unsteady aerodynamic force, it is necessary first to deformed gas
Dynamic face carries out grid dividing.Grid dividing standard can refer to the grid dividing requirement of panel method, generally require grid favorable current side
To not interlocking unanimously, grid slenderness ratio is suitable.Pneumatic surface grids should not it is too close can not be too thick.Tangential grid is at least more than 5, exhibition
It can be determined to grid according to grid cell slenderness ratio.
After carrying out grid dividing to deformed pneumatic face, need to carry out aircraft structural dynamical model to obtain
Take structural elasticity mode.In the present invention, the structural dynamical model of aircraft can be used general business software and carry out, such as
MSC.NASTRAN, ABAQUS etc..
Further, in the present invention, carrying out structural elasticity mode acquired in structural dynamical model to aircraft can
It can be unrelated with pneumatic face.For example, pneumatic face is wing for aircraft, but the solution of structural elasticity mode can be started
The mode such as machine, undercarriage, these are unrelated with pneumatic face, are not required to consider these mode when carrying out unsteady aerodynamic force calculating, only
Need structural modal relevant to pneumatic face.Therefore, the pneumatic face after extracting deformation in the structural elasticity mode of aircraft
Relevant structural elasticity mode is simultaneously interpolated into after deformation on the pneumatically aerodynamic grid in face.
Then, in space, pneumatic surface grids arrange dipole elementary solution, for that should meet at 3/4 chord length point in each grid
Following integral equationWherein, ρ is that incoming flow is close
Degree, V is speed of incoming flow, wiFor the downwash velocity at i-th of 3/4 chord length point of grid, Δ xjFor the middle length profile of j-th of grid,
ljFor length (Fig. 4 of the 1/4 string point of mistake of j-th of grid),For angle of sweep (Fig. 4 of j-th of gridSweepback
Angle), KijFor the kernel function of aerodynamics evaluation, n is the aerodynamic grid block count of lifting surface,For the pressure on j-th of grid
Coefficient,With pressure Δ pjBetween relationship be
The kernel function for considering the deformation of pneumatic face is λ1=x-xj, wherein (xi,yi,zi) it is receiving point coordinate, (xj,yj,zj) it is that disturbance point is sat
Mark,niIt is (xi,yi,zi) at aerofoil normal direction, njIt is (xj,yj,zj) at the wing
Face normal direction, ω are structural vibration circular frequency, U∞For distant place speed of incoming flow, R' is the distance between receiving point and disturbance point,
a∞For the velocity of sound of remote front incoming flow, M∞For free stream Mach number.In space curved surface lifting surface, ni, njIt is that space arbitrarily may be to
Amount, it is determining in the local coordinate system of respective grid respectively, With the shape of aerofoil grid in space (as bending becomes
Shape, torsional deflection) it is related.The geological information (such as upper counterangle, angle of sweep, torsion angle) of each grid of curved surface lifting surface is no
Equally, it needs constantly to be updated, just can be suitably used for the calculating of large deformation wing curved surface unsteady aerodynamic force.Consider having acquired
After the kernel function of pneumatic face deformation, space curved surface dipole influence coefficient matrix D can be calculated according to kernel function.
After calculating the kernel function for obtaining the pneumatic face deformation of consideration, need to calculate the local normal direction of the pneumatic surface grids of curved surface
Amount.Specifically, the local normal vector of the pneumatic surface grids of curved surface can be obtained with two vector multiplication crosses of grid.
After the local normal vector for obtaining the pneumatic surface grids of curved surface, will be interpolated into the structural elasticity mode in pneumatic face with
The normal direction mode in pneumatic face after local normal vector multiplication can be deformed.N' indicates the method for curved surface aerodynamic grid S (x, y, z)=0
Vector, (n', x), (n', y), (n', z) are the angle of normal and reference axis, it is assumed that the forms of motion of curved surface aerodynamic grid is S=
Seiwt, then the normal velocity of object of which movement beIt should
Formula is pervasive curved surface aerodynamic grid boundary condition.Consider normal direction Motion correction normal direction kinematical boundary condition beWherein, w is grid dimensionless normal direction downwash velocity, and k is reduced frequency, and b is with reference to chord length, and f is after deforming
The normal direction mode in pneumatic face, n' are curved surface normal direction,For real part,For imaginary part.
After obtaining normal direction kinematical boundary condition, to the downwash velocity equation in each grid at 3/4 chord length pointArrange and can obtain w=D Δ cp, after deformation
Unsteady aerodynamic force Δ c on pneumatic surface gridspIt can be according to w=D Δ cpTo obtain, wherein w is to wash under grid dimensionless normal direction
Speed, D are aerodynamic influence matrix, Δ cpThe column vector formed for the unsteady aerodynamic force of aerodynamic grid.Specifically, exist
In the present invention, aerodynamic influence matrix D can basisTo solve, wherein Δ xjFor jth
The middle length profile of a grid, ljFor the length of the 1/4 string point of mistake of j-th of grid, χjFor 1/4 string angle of sweep of grid, KijFor
Kernel function.
It further, will be on surface grids pneumatic after deformation after the unsteady aerodynamic force for obtaining the pneumatic face of curved surface
The normal direction mode in pneumatic face is multiplied to obtain the curved surface unsteady aerodynamic force of generalization after unsteady aerodynamic force and deformation.As a result,
Complete the acquisition of the curved surface unsteady aerodynamic force of generalization.According to the curved surface unsteady aerodynamic force of acquired generalization,
It can carry out subsequent flutter analysis or aeroelastic divergence analysis.
From the foregoing, it will be observed that the present invention provides a kind of frequency domain for considering pneumatic face curved surface effect and normal direction movement is unsteady pneumatic
Power calculation method, the division of three-dimensional pneumatic surface grids not only can be special with the pneumatic face bending of accurate description, the geometry of torsional deflection
Point, the introducing based on local normal direction mode have been truly reflected the pneumatic face of curved surface and effective normal direction of unsteady aerodynamic force are caused to be transported
It is dynamic.Curved surface effect and normal direction movement characteristic are embodied in terms of the determination two of the Modeling Calculation in pneumatic face and boundary condition, are adapted to
The calculating demand of flexible flier curved surface frequency domain unsteady aerodynamic force is subsequent flutter, aeroelasticity dynamic response and pneumatic servo
The input of flexibility analysis provides guarantee.
Further understand to have to the present invention, the pneumatic face curved surface of consideration of the invention is imitated below with reference to Fig. 1 to Fig. 7
The frequency domain unsteady aerodynamic force calculation method that should be moved with normal direction is described in detail.
As a specific embodiment of the invention, as shown in Figures 1 to 7, by taking a high aspect ratio rectangular wing as an example,
The frequency domain unsteady aerodynamic force calculation method moved to consideration curved surface effect of the invention and normal direction is introduced.Airfoil chord is a length of
60mm, length 480mm.Since example is high aspect ratio wing, using symmetrical airfoil, do not consider that camber influences, wing
It is deformed into space curved surface under load effect, as shown in Figure 5.Only method applicable cases are illustrated herein, therefore are selected
Example is relatively simple, and pneumatic face divides more coarse.Practical application is should be more careful according to the requirement of technical solution progress
Pneumatic face divides and modeling.Steps are as follows for concrete analysis.
Step 1 divides the enterprising promoting the circulation of qi dynamic mesh in face pneumatic after the deformation of aircraft.
Step 2 carries out structural dynamical model to aircraft to obtain the structural elasticity mode of aircraft.
Step 3, simultaneously from the structural elasticity mode relevant to face pneumatic after deformation of extraction in the structural elasticity mode of aircraft
It is interpolated into after deformation on the pneumatically aerodynamic grid in face.
Step 4, after deformation arrangement space dipole elementary solution on each grid in pneumatic face, wherein F1, F3 are gas
The intersection point of dynamic mesh Europe dipole sub-line and aerodynamic grid.F2 is the position of unsteady aerodynamic force, is the midpoint of F1, F3, and H is
The control point of aerodynamic grid.The kernel function for considering pneumatic face deformation is solved, aerodynamic influence matrix is solved according to kernel function.
Step 5 calculates the local normal vector of the aerodynamic grid in pneumatic face after deforming.
The structural elasticity mode in face pneumatic after deformation and local normal vector are multiplied to pneumatic face after acquisition deforms by step 6
Normal direction mode, according to the normal direction mode in face pneumatic after deformation solve normal direction kinematical boundary condition.
Step 7 is solved after deforming according to normal direction kinematical boundary condition and aerodynamic influence matrix on pneumatic surface grids
Unsteady aerodynamic force.
Unsteady aerodynamic force on surface grids pneumatic after deformation is multiplied by step 8 with the normal direction mode in face pneumatic after deformation
To obtain the curved surface unsteady aerodynamic force of the generalization in frequency domain.
After obtaining the curved surface unsteady aerodynamic force of generalization, flutter is carried out using obtained unsteady aerodynamic force
It calculates.
In conclusion the present invention provides a kind of unsteady aerodynamic force meters for considering pneumatic face curved surface effect and normal direction movement
Calculation method, this method not only carries out accurate description from the pneumatic face of curved surface of the Geometric Modeling level to deformation, and this curved surface is imitated
It should be introduced into the calculating of aerodynamic influence matrix kernel function, inherently consider the deformed curved surface effect in pneumatic face
It influences.Furthermore influence of the effective normal direction component motion in the pneumatic face of curved surface in unsteady aerodynamic force calculating is also contemplated, from boundary
The accurate description of condition is started with, and the calculating of curved surface unsteady aerodynamic force is carried out.Unsteady aerodynamic force provided by the present invention calculates
Method compared with prior art, has the following advantages that.
First, unsteady aerodynamic force calculation method of the invention carries out the division of three-dimensional pneumatic surface grids in space, can be quasi-
The really geometrical characteristic of the bending of description lifting surface, torsion, the modeling suitable for aerodynamic force under the various movements of aircraft and deformation state
It calculates.
Second, pneumatic face curved surface effect is introduced the sky of dipole elementary solution by unsteady aerodynamic force calculation method of the invention
Between arrange and kernel function calculating in, sufficiently reflect unsteady aerodynamic force calculate in curved surface effect.
Third, unsteady aerodynamic force calculation method of the invention introduce the method for pneumatic face locality in frequency domain aerodynamics evaluation
To mode of motion, accurate description causes the effective normal direction forms of motion and Normal interface condition of unsteady aerodynamic force.
For ease of description, spatially relative term can be used herein, as " ... on ", " ... top ",
" ... upper surface ", " above " etc., for describing such as a device shown in the figure or feature and other devices or spy
The spatial relation of sign.It should be understood that spatially relative term is intended to comprising the orientation in addition to device described in figure
Except different direction in use or operation.For example, being described as if the device in attached drawing is squeezed " in other devices
It will be positioned as " under other devices or construction after part or construction top " or the device of " on other devices or construction "
Side " or " under other devices or construction ".Thus, exemplary term " ... top " may include " ... top " and
" in ... lower section " two kinds of orientation.The device can also be positioned with other different modes and (is rotated by 90 ° or in other orientation), and
And respective explanations are made to the opposite description in space used herein above.
In addition, it should be noted that, limiting components using the words such as " first ", " second ", it is only for be convenient for
Corresponding components are distinguished, do not have Stated otherwise such as, there is no particular meanings for above-mentioned word, therefore should not be understood as to this
The limitation of invention protection scope.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (8)
1. a kind of unsteady aerodynamic force calculation method for considering pneumatic face curved surface effect and normal direction movement, which is characterized in that described
Unsteady aerodynamic force calculation method includes:
Grid dividing is carried out to face pneumatic after the deformation of aircraft；
Structural dynamical model is carried out to obtain the structural elasticity mode of aircraft to aircraft；
From the structural elasticity mode relevant to face pneumatic after deformation of extraction in the structural elasticity mode of the aircraft and it is interpolated into
After deformation on the aerodynamic grid in pneumatic face；
Dipole elementary solution is arranged on the grid in pneumatic face after deformation, the kernel function for considering pneumatic face deformation is solved, according to institute
It states kernel function and solves aerodynamic influence matrix；
Calculate the local normal vector of the aerodynamic grid in pneumatic face after deforming；
The normal direction mode that pneumatic face after deformation is solved according to the structural elasticity mode in face pneumatic after deformation and local normal vector, according to
The normal direction mode in pneumatic face solves normal direction kinematical boundary condition after deformation；
It is solved according to the normal direction kinematical boundary condition and the aerodynamic influence matrix after deforming on pneumatic surface grids
Unsteady aerodynamic force；
According to the normal direction mode in the unsteady aerodynamic force on surface grids pneumatic after deformation and pneumatic face after deformation to obtain generalization
Curved surface unsteady aerodynamic force.
2. the unsteady aerodynamic force calculation method according to claim 1 for considering pneumatic face curved surface effect and normal direction movement,
It is characterized in that, considering that the kernel function of pneumatic face deformation isλ1=x-xj, wherein
(xi,yi,zi) it is receiving point coordinate, (xj,yj,zj) it is disturbance point coordinate,niIt is
(xi,yi,zi) at aerofoil normal direction, njIt is (xj,yj,zj) at aerofoil normal direction, ω be structural vibration circular frequency, U∞
For distant place speed of incoming flow, R' is the distance between receiving point and disturbance point, a∞For the velocity of sound of remote front incoming flow, M∞For incoming flow Mach
Number.
3. the unsteady aerodynamic force calculation method according to claim 2 for considering pneumatic face curved surface effect and normal direction movement,
It is characterized in that, after the deformation pneumatic face normal direction mode f can according to the structural elasticity mode in face pneumatic after deformation with it is described
Local normal vector is multiplied to obtain.
4. the unsteady aerodynamic force calculation method according to claim 3 for considering pneumatic face curved surface effect and normal direction movement,
It is characterized in that, the normal direction kinematical boundary condition isWherein, w is grid dimensionless normal direction downwash velocity,
K is reduced frequency, and b is with reference to chord length, and f is the normal direction mode in pneumatic face after the deformation, and n' is curved surface normal direction,For real part,For imaginary part.
5. the unsteady aerodynamic force calculation method according to claim 4 for considering pneumatic face curved surface effect and normal direction movement,
It is characterized in that, the unsteady aerodynamic force Δ c after deformation on pneumatic surface gridspIt can be according to w=D Δ cpTo obtain, wherein w is net
Lattice dimensionless normal direction downwash velocity, D are aerodynamic influence matrix, Δ cpFor aerodynamic grid unsteady aerodynamic force form
Column vector.
6. the unsteady aerodynamic force calculation method according to claim 5 for considering pneumatic face curved surface effect and normal direction movement,
It is characterized in that, the aerodynamic influence matrix D can basisTo solve, wherein Δ xj
For the middle length profile of j-th of grid, ljFor the length of the 1/4 string point of mistake of j-th of grid, χjFor 1/4 string angle of sweep of grid,
KijFor kernel function.
7. according to any one of claim 1 to 6 consider the unsteady pneumatic of pneumatic face curved surface effect and normal direction movement
Power calculation method, which is characterized in that in said step 1, the tangential grid in pneumatic face is at least more than 5, Zhan Xiang after the deformation
Grid can be determined according to grid cell slenderness ratio.
8. the unsteady aerodynamic force calculation method according to claim 7 for considering pneumatic face curved surface effect and normal direction movement,
It is characterized in that, the curved surface unsteady aerodynamic force of the generalization can be according to the unsteady aerodynamic force on surface grids pneumatic after deformation
It is multiplied with the normal direction mode in face pneumatic after the deformation to obtain.
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