CN105912762A - Method and device for determining load distribution of aircraft wing surface - Google Patents

Method and device for determining load distribution of aircraft wing surface Download PDF

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Publication number
CN105912762A
CN105912762A CN201610211106.5A CN201610211106A CN105912762A CN 105912762 A CN105912762 A CN 105912762A CN 201610211106 A CN201610211106 A CN 201610211106A CN 105912762 A CN105912762 A CN 105912762A
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finite element
load
element point
point
aerofoil
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CN105912762B (en
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牟全臣
白绍鹏
姚立民
任如飞
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Universal Software (beijing) Co Ltd
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Universal Software (beijing) Co Ltd
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Abstract

The invention provides a method and device for determining load distribution of an aircraft wing surface. The method includes: determining all the finite element pointes to be calculated and included in the aircraft wing surface; acquiring a coordinate and a CP value corresponding to each test point on the wing surface; determining a first calculation coefficient according to the coordinates and the CP values corresponding to all the test points, and calculating a first load corresponding to each finite element point on the wing surface according to a preset rule; calculating the total load according to the first loads corresponding to all the finite element points, and comparing the total load and a total input load to determine a distribution error; determining a second calculation coefficient according to the distribution error, the first loads corresponding to all the finite element pointes and the coordinates of all the finite element points on the wing surface; and determining a second load corresponding to each finite element point according to the second calculation coefficient, the first load and the coordinate of each finite element point on the wing surface. The method for determining load distribution of the aircraft wing surface can ensure the reasonability of aerodynamic load distribution.

Description

A kind of method and apparatus determining that plane airfoil load is distributed
Technical field
The present invention relates to the computing technique field of aircraft wing finite element point load, particularly relate to one and determine the aircraft wing The method and apparatus of face load distribution.
Background technology
Plane airfoil structure needs the load born to include aerodynamic loading, inertial load and concentration power load.Having Limit unit needs to map aerodynamic loading, inertial load and concentration power load on finite element point when calculating, and mapping result need to meet Total load is equal with total moment, pressure heart invariant position.Owing to mapping method is a kind of numerical method, there is assignment accuracy problem, need Load after distribution will be carried out trim and load sharing, different method for solving has Different Results, therefore airfoil structure finite element On point, the verity of load distribution is the premise of full machine finite element solving result accuracy.
At present, on more conventional finite element point, the allocative decision of load is 3 row's schemes, and 3 row's schemes are exactly will Load distribution on one pneumatic point is on 3 neighbouring finite element points, and these 3 finite element points need to meet following 3 requirements: Ask one, 3 finite element points must not conllinear；Require that two, 3 finite element points must be nearest from pneumatic some A；Requirement three, pneumatic some A In the region of the triangle that must be positioned at 3 finite element point compositions.
It is 1,2,3 with three finite element points, as a example by pneumatic point is A, with reference to Fig. 1,3 row's schemes is illustrated.The party Case needs to collect all of point, and each point is all required for by formulaProcess the load being calculated distribution, right In the load of unit conode, directly it is added, the pneumatic node load map to finite element point can be completed.Wherein, j=1,2, 3 is the mark of three finite element points, PA: the load on pneumatic some A, A is the area of triangle 123, A1: the face of triangle A23 Long-pending, A2: the area of triangle A13, A3: the area of triangle A12.
3 row's schemes need the condition met the harshest, for some pneumatic points, find nearest 3 finite element Point, does not but fall within the delta-shaped region of its composition, and distribution cannot process, it is impossible to ensure the reasonability of distribution.Visible, existing Plane airfoil on the allocative decision of finite element point load cannot ensure the reasonability of distribution, namely the accuracy of load distribution Difference.
Summary of the invention
In view of the above-mentioned existing scheme determining that plane airfoil load is distributed cannot ensure the rational problem of distribution, carry Go out the present invention to provide a kind of determination plane airfoil load overcoming the problems referred to above or solving the problems referred to above at least in part The method and apparatus of lotus distribution.
According to one aspect of the present invention, it is provided that a kind of method determining that plane airfoil load is distributed, comprise determining that and treat Each finite element point that the plane airfoil calculated comprises；Obtain coordinate and CP value that on described aerofoil, each testing site is corresponding；Foundation Coordinate and CP value that each testing site is corresponding determine the first design factor；According to described first design factor according to setting rule meter Calculate the first load that on described aerofoil, each finite element point is corresponding；According to aerofoil described in the first LOAD FOR that each finite element point is corresponding Full payload, and described full payload is compared with total input load, determines distribution error；According to described distribution error, respectively The first load and each finite element point coordinate on aerofoil that finite element point is corresponding determine the second design factor；Have for each Limit unit point, according to the second design factor, the first load and finite element point coordinate on aerofoil, determines that finite element point is corresponding Second load.
Preferably, the described coordinate corresponding according to each testing site and CP value determine that the step of the first design factor includes: Coordinate and the first design factor according to each testing site build the first matrix；According to the CP value structure second that each testing site is corresponding Matrix；The 3rd matrix is determined by the first matrix and the second matrix；Each matrix element in 3rd matrix is defined as the first meter Calculate coefficient.
Preferably, described each finite element point pair on described aerofoil is calculated according to described first design factor according to setting rule The step of the first load answered includes: be grouped according to FEM (finite element) model by the finite element point on described aerofoil；For often group Each finite element point in finite element point determines the first load of correspondence according to setting rule.
Preferably, the first corresponding load is determined for each finite element point often organized in finite element point according to setting rule Step comprises determining that the cell type of unit associated by current group finite element point；The list of unit associated by current group finite element point When element type is tetragon, tetragon is diagonally divided into four trianglees；Calculate having at each triangular apex respectively The testing site separate loading that limit unit point is corresponding；For each finite element point, according to testing site separate loading corresponding to finite element point, gravity Acceleration and ram compression coefficient determine the first load.
Preferably, for each finite element point, foundation the second design factor, the first load and finite element point are on aerofoil Coordinate, determine that the step of the second load that finite element point is corresponding includes: determine that finite element point is corresponding by below equation Two load: Fx=Fx+Fx×(a0+a1×Xx+a2×Yx)；Wherein, x is positive integer variable, FxFor x-th finite element point first Load, XxFor the abscissa of x-th finite element point, YxFor the vertical coordinate of x-th finite element point, a0、a1、a2It it is the second calculating system Number.
Preferably, described for each finite element point, exist according to the second design factor, the first load and finite element point Coordinate on aerofoil, after determining the step of the second load that finite element point is corresponding, described method also includes: second will determined Load carries out corresponding storage with finite element point, and generates the text of specific format.
According to one aspect of the present invention, additionally provide a kind of device determining that plane airfoil load is distributed, comprise determining that Module, for determining each finite element point that plane airfoil to be calculated comprises；Acquisition module, is used for obtaining on described aerofoil and respectively tries Test a corresponding coordinate and CP value；First coefficient determination module, true for the coordinate corresponding according to each testing site and CP value Fixed first design factor；First load determines module, for calculating described according to described first design factor according to setting rule The first load that on aerofoil, each finite element point is corresponding；Error determination module, for first load corresponding according to each finite element point Calculate the full payload of described aerofoil, and described full payload is compared with total input load, determine distribution error；Second coefficient Determine module, for first load corresponding according to described distribution error, each finite element point and each finite element point at aerofoil Coordinate determine the second design factor；Second load determines module, for for each finite element point, calculating system according to second Number, the first load and finite element point coordinate on aerofoil, determine the second load that finite element point is corresponding.
Preferably, described first coefficient determination module includes: the first submodule, for according to each testing site coordinate and First design factor builds the first matrix；Second submodule, builds the second matrix for the CP value corresponding according to each testing site；The Three submodules, for determining the 3rd matrix by the first matrix and the second matrix；4th submodule, in the 3rd matrix Each matrix element is defined as the first design factor.
Preferably, described first load determines that module includes: packet submodule, for by the finite element point on described aerofoil It is grouped according to FEM (finite element) model；Load determines submodule, for for each finite element point often organized in finite element point according to Set rule and determine the first load of correspondence.
Preferably, load determine submodule for each finite element point often organizing in finite element point according to set rule determine right During the first load answered: determine the cell type of unit associated by current group finite element point；List associated by current group finite element point When the cell type of unit is tetragon, tetragon is diagonally divided into four trianglees；Calculate each triangular apex respectively The testing site separate loading corresponding to finite element point at place；For each finite element point, according to the testing site load sharing that finite element point is corresponding Lotus, acceleration of gravity and ram compression coefficient determine the first load.
Preferably, described second load determines that module is for each finite element point, foundation the second design factor, the first load And the coordinate that finite element point is on aerofoil, when determining the second load corresponding to finite element point: determined limited by below equation The second load that unit's point is corresponding: Fx=Fx+Fx×(a0+a1×Xx+a2×Yx)；Wherein, x is positive integer variable, FxHave for x-th First load of limit unit point, XxFor the abscissa of x-th finite element point, YxFor the vertical coordinate of i-th finite element point, a0、a1、a2For Second design factor.
Preferably, described device also includes: text generation module, for determining that module is at described pin in described second load To each finite element point, according to the second design factor, the first load and finite element point coordinate on aerofoil, determine finite element After the second load that point is corresponding, the second load determined is carried out with finite element point corresponding storage, and generates specific format Text.
The scheme of the determination plane airfoil load distribution that the embodiment of the present invention provides, by automatic for the aerodynamic loading on testing site Be assigned on finite element point, be to consider according to finite element node coordinate position, therefore have the strongest practicality and Reasonability.Moreover, the distribution scheme that the embodiment of the present invention provides, owing to being automatically to be carried out aerodynamic loading by calculating equipment Distribution, and without participating in manually, therefore, the accuracy of result of calculation is high.Another further aspect, is calculating on each finite element point After the load of distribution, determine distribution error according to total input load, according to distribution error, the load of distribution on each finite point is entered Row is revised, it is possible to the pressure realizing distributing always carries and always carries with input pressure equal and press heart position identical, thus ensures pneumatic load The reasonability of lotus distribution.
Described above is only the general introduction of technical solution of the present invention, in order to better understand the technological means of the present invention, And can be practiced according to the content of description, and in order to allow above and other objects of the present invention, the feature and advantage can Become apparent, below especially exemplified by the detailed description of the invention of the present invention.
Accompanying drawing explanation
By reading the detailed description of hereafter preferred implementation, various other advantage and benefit common for this area Technical staff will be clear from understanding.Accompanying drawing is only used for illustrating the purpose of preferred implementation, and is not considered as the present invention Restriction.And in whole accompanying drawing, it is denoted by the same reference numerals identical parts.In the accompanying drawings:
Fig. 1 is the delta-shaped region of testing site and finite element point composition；
Fig. 2 is a kind of flow chart of steps determining method that plane airfoil load is distributed of according to embodiments of the present invention；
Fig. 3 is a kind of flow chart of steps determining method that plane airfoil load is distributed of according to embodiments of the present invention two；
Fig. 4 is the distribution schematic diagram of testing site on wing single-blade face；
Fig. 5 is the distribution schematic diagram of finite element point on wing single-blade face；
Fig. 6 is a kind of structured flowchart determining device that plane airfoil load is distributed of according to embodiments of the present invention three；
Fig. 7 is a kind of structured flowchart determining device that plane airfoil load is distributed of according to embodiments of the present invention four.
Detailed description of the invention
It is more fully described the exemplary embodiment of the disclosure below with reference to accompanying drawings.Although accompanying drawing shows the disclosure Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure and should be by embodiments set forth here Limited.On the contrary, it is provided that these embodiments are able to be best understood from the disclosure, and can be by the scope of the present disclosure Complete conveys to those skilled in the art.
Embodiment one
With reference to Fig. 2, it is shown that the embodiment of the present invention one a kind of determines the step stream of the method that plane airfoil load is distributed Cheng Tu.
The method of the determination plane airfoil load distribution of the embodiment of the present invention comprises the following steps:
Step S102: determine each finite element point that plane airfoil to be calculated comprises.
In actual application, need to calculate the load of the port wing above and below of aircraft, and starboard wing above and below Load.In the embodiment of the present invention, illustrate as a example by calculating the one side on the wing of aircraft one side.Implementing process In, repeat to use the method provided in the embodiment of the present invention, i.e. can determine that each airfoil load distribution situation.
The finite element node of the upper lower aerofoil of left and right wing is grouped, is divided into upper left, lower-left, upper right bottom right aerofoil pair Answer finite element point group, in order to carry out load correction trim.When determining that a certain airfoil load is distributed, then need first to obtain this wing The finite element point that face is corresponding, i.e. determines each finite element point that plane airfoil to be calculated comprises.
Step S104: obtain coordinate and CP value that on aerofoil, each testing site is corresponding.
Wherein, CP value i.e. loading coefficient.
It is not provided only with finite element point on aerofoil, is additionally provided with testing site.In the process determining that plane airfoil load is distributed In, in addition it is also necessary to obtain coordinate corresponding to each testing site and CP value.
Step S106: the coordinate corresponding according to each testing site and CP value determine the first design factor.
When determining the first design factor, the first design factor can be determined by the form building matrix equation.The present invention In embodiment, for how building matrix equation it is not specifically limited, during implementing, can be by people in the art Member is determined according to the actual requirements.
Step S108: calculate, according to setting rule, the first load that each finite element point on aerofoil is corresponding according to the first design factor Lotus.
When calculating the first load that on aerofoil, each finite element point is corresponding, can be by the finite element point on aerofoil according to finite element Model is grouped, and in packetized units, calculates the first load that in each group, each finite element point is corresponding respectively.
Step S110: according to the full payload of the first LOAD FOR aerofoil corresponding to each finite element point, and by full payload with total Input load compares, and determines distribution error.
The mode calculating aerofoil full payload of a kind of feasibility is as follows: owing to each finite element point is to having coordinate, Yi Ji One load, it is consequently possible to calculate finite element point is positioned at the load of making a concerted effort at (0,0,0) point, will close calculated load of making a concerted effort It is defined as the full payload of aerofoil.
Total input load is preset value, is by the value in staff's input to calculating equipment, be may determine that by this value The distribution error of the first load that each finite element point of determining in step S108 is corresponding.Need logical to obtain aerofoil more accurately Crossing distribution error to be modified the first load that each finite element point is corresponding, concrete correcting mode is as shown in follow-up flow process.
Step S112: first load corresponding according to distribution error, each finite element point and each finite element point are on aerofoil Coordinate determine the second design factor.
When determining the second design factor, the second design factor can be determined by the form building matrix equation.The present invention In embodiment, for how building matrix equation it is not specifically limited, during implementing, can be by people in the art Member is determined according to the actual requirements.
Step S114: for each finite element point, foundation the second design factor, the first load and finite element point are at aerofoil On coordinate, determine the second load that finite element point is corresponding.
A kind of preferred foundation the second design factor, the first load and finite element point coordinate on aerofoil, determine and have The mode of the second load that limit unit point is corresponding is as follows:
The second load that finite element point is corresponding: F is determined by below equationx=Fx+Fx×(a0+a1×Xx+a2×Yx)；Its In, x is positive integer variable, FxFor the first load of x-th finite element point, XxFor the abscissa of x-th finite element point, YxFor xth The vertical coordinate of individual finite element point, a0、a1、a2It it is the second design factor.
The second load that each finite element point that the embodiment of the present invention finally determines is corresponding can reflect plane airfoil load Distribution situation.
By the method for the determination plane airfoil load distribution that the embodiment of the present invention provides, by the aerodynamic loading on testing site Be automatically assigned on finite element point, be to consider according to finite element node coordinate position, therefore have the strongest practicality, And reasonability.Moreover, the distribution scheme that the embodiment of the present invention provides, owing to being automatically to aerodynamic loading by calculating equipment It is distributed, and without participating in manually, therefore, the accuracy of result of calculation is high.Another further aspect, is calculating each finite element On point after the load of distribution, determine distribution error according to total input load, according to distribution error to the load of distribution on each finite point Lotus is modified, it is possible to the pressure realizing distributing always carries and always carries with input pressure equal and press heart position identical, thus ensures gas The reasonability of dynamic load distribution.
Embodiment two
With reference to Fig. 3, it is shown that the embodiment of the present invention two a kind of determines the step stream of the method that plane airfoil load is distributed Cheng Tu.
The method of the determination plane airfoil load distribution of the embodiment of the present invention comprises the following steps:
Step S202: determine each finite element point that plane airfoil to be calculated comprises.
In actual application, need to calculate the load of the port wing above and below of aircraft, and starboard wing above and below Load.In the embodiment of the present invention, illustrate as a example by calculating the one side on the wing of aircraft one side.Implementing process In, repeat to use the method provided in the embodiment of the present invention, i.e. can determine that each airfoil load distribution situation.
The finite element node of the upper lower aerofoil of left and right wing is grouped, is divided into upper left, lower-left, upper right bottom right aerofoil pair Answer finite element point group, in order to carry out load correction trim.When determining that a certain airfoil load is distributed, then need first to obtain this wing The finite element point that face is corresponding, i.e. determines each finite element point that plane airfoil to be calculated comprises.
Step S204: obtain coordinate and CP value that on aerofoil, each testing site is corresponding.
Wherein, testing site distribution schematic diagram on aerofoil as shown in Figure 4, finite element point scattergram on plane airfoil Schematic diagram is as shown in Figure 5.
Step S206: the coordinate corresponding according to each testing site and CP value determine the first design factor.
A kind of preferred coordinate corresponding according to each testing site and CP value determine that the mode of the first design factor is as follows: depend on Coordinate and the first design factor according to each testing site build the first matrix；The CP value corresponding according to each testing site builds the second square Battle array；The 3rd matrix is determined by the first matrix and the second matrix；Each matrix element in 3rd matrix is defined as the first calculating Coefficient.
A kind of specific implementation for this optimal way is as follows: in this instantiation, sets testing site sum as n.
First, pass throughCalculate the r that each testing site is correspondingij 2.Wherein, x in formulaiRepresent The abscissa of i-th testing site, yiRepresent the vertical coordinate of i-th testing site.X in formulajRepresent the abscissa of jth experimental point, yj Representing the vertical coordinate of jth testing site, i, j are positive integer.
Secondly, by the r that each testing site is correspondingij 2, and coordinate corresponding to each testing site, CP value build matrix equation, Constructed matrix equation is as follows:
0 r 12 2 . lnr 12 2 r 13 2 . lnr 13 2 .... r 1 n 2 . lnr 1 n 2 1 x 1 y 1 r 21 2 . lnr 21 2 0 r 23 2 . lnr 23 2 r 2 n 2 . lnr 2 n 2 1 x 2 y 2 ... ... ... ... r n 1 2 . lnr n 1 2 r n 2 2 . lnr n 2 2 0 1 x n y n 1 1 1 ... 1 0 0 0 x 1 x 2 ... ... x n 0 0 0 y 1 y 2 ... ... y n 0 0 0 · f 1 f 2 f n b 0 b 1 b 2 = P 1 P 2 P n 0 0 0
Wherein, the matrix on the left side is the first matrix, and the matrix on the right is the second matrix, and middle matrix is the 3rd matrix.
P1It is the CP value of first testing site, PnIt is the CP value of the n-th testing site, f1To fn, b0, b1,b2For required One design factor.
After determining the first design factor, then need to determine that on aerofoil, each finite element point is corresponding according to the first design factor Load, specifically determine that mode is as described below.
Step S208: the finite element point on aerofoil is grouped according to FEM (finite element) model.
When packet, being grouped according to FEM (finite element) model by finite element point, the cell type of FEM (finite element) model includes four Limit shape unit and triangular element.
Step S210: determine that the first of correspondence carries according to setting rule for each finite element point often organized in finite element point Lotus.
A kind of the first load preferably determining correspondence for each finite element point in one group of finite element point according to setting rule The mode of lotus is as follows:
S1: determine the cell type of unit associated by current group finite element point；
Cell type in finite element point group can be divided into tetragon and triangle according to FEM (finite element) model, and this is the most square Formula illustrates as a example by the cell type of current group finite element point is as tetragon.
S2: when the cell type of unit is tetragon associated by current group finite element point, tetragon is diagonally divided Become four trianglees；
For this group finite element point, the tetragon that finite element point surrounds diagonally is divided into 4 trianglees, if four Finite element point is respectively i, j, k, w (i, j, k, w represent four positive integers of continuous print), and i, j, k, w arranged clockwise surrounds four limits Shape, the triangle that four trianglees respectively i, j, k after division surround, the triangle that j, k, w surround, k, w, i surround three The triangle that dihedral and w, i, j surround.
S3: calculate the testing site separate loading that the finite element point at each triangular apex is corresponding respectively；
The first step, calculates the q value that in triangle, the finite element point of each apex is corresponding.
Illustrate as a example by the q value that i, j, k finite element point in the triangle surrounded calculating i, j, k is corresponding below.
Pass through formula:
Determine the q that i point is correspondingi, the q of j point correspondencej, the q of k point correspondencek。
q x = b 0 + b 1 + b 2 × y x + Σ i = 1 n f i × [ ( x e - x x ) + ( y e - y x ) ] × L n ( [ ( x e - x x ) 2 + ( y e - y x ) 2 ] )
Wherein, the coordinate of finite element point is xx, yx；xe, yeCoordinate for testing site.E is arranged to by above-mentioned formula For indicating the variable positive integer of different tests point, and, the value of e is 1 to n.X is used for indicating different finite element point.So, Owing to this step needing calculate the testing site load sharing that tri-finite element points of i, j and k are corresponding, therefore, need above-mentioned during calculating The positive integer that x variable in formula takes i, j corresponding with k respectively substitutes.By i, j and k being substituted respectively above-mentioned formula In little x can calculate qi、qj、qk。
Second step, calculates CP value p of finite element point i respectively by equation belowiI.e. testing site separate loading, finite element point j CP value pj, CP value p of finite element point kk。
p i = S × q i + q j + q k + q i 12 ;
p j = S × q i + q j + q k + q j 12 ;
p k = S × q i + q j + q k + q k 12 ;
Wherein, S is the area of the triangle that finite element point i, j, k surround.
Repeat the first step and second step, determine the CP value that the finite element point at each vertex of a triangle is corresponding, i.e. By the some calculating of finite element in four trianglees can be obtained 12 CP values, say, that each finite element point is by correspondence three Individual CP value, as a example by i point, then corresponding pi1、pi2、pi3Three CP values.
3rd step, determines, by equation below, the final testing site separate loading that finite element point is corresponding.
p x = p x 1 + p x 2 + p x 3 2 ;
Wherein, x still for the variable positive integer for indicating different finite element point, in this step x take i, j and k can be really Make the experimental point separate loading p that tri-finite element points of i, j and k are the most correspondingi、pj、pk。
The mode of the determination finite element point described in repeated execution of steps S3, i.e. can determine that three apex of each triangle Testing site load sharing corresponding to finite element point.
It should be noted that when the shape that finite element point group surrounds is not four limit row but during triangle, determine finite element When putting corresponding testing site separate loading, it is not necessary to divide, without performing the 3rd step, but directly perform first in S3 Step, second step i.e. can determine that the testing site load sharing that three finite element points are corresponding.
S4: for each finite element point, according to testing site separate loading, acceleration of gravity and ram compression that finite element point is corresponding Coefficient determines the first load.
Especially by the first load that equation below calculating finite element point is corresponding:
Fx=px×g×Vp
Wherein, FxIt is the first load, pxFor testing site separate loading, VpFor ram compression coefficient.X is still for being used for indicating difference to have The variable positive integer of limit unit point, in this step, x takes that i, j i.e. can determine that with k that tri-finite element points of i, j and k are the most corresponding One load Fx、FjAnd Fk。
Repeat above-mentioned S1 to S3, can be true by the first corresponding for each finite element point of often organizing in finite element point load Fix.
Step S212: according to the full payload of the first LOAD FOR aerofoil corresponding to each finite element point, and by full payload with total Input load compares, and determines distribution error.
Step S214: first load corresponding according to distribution error, each finite element point and each finite element point are on aerofoil Coordinate determine the second design factor.
Wherein, the second design factor i.e. weight coefficient.
A kind of preferably determine the second design factor mode be: calculated by following matrix equation.
Σ i = 1 n F i Σ i = 1 n F i · x i Σ i = 1 n F i · y i - Σ i = 1 n F i · x i - Σ i = 1 n F i · x i 2 - Σ i = 1 n F i · x i y i Σ i = 1 n F i · y i Σ i = 1 n F i · x i y i Σ i = 1 n F i · y i 2 · a 0 a 1 a 2 = F - Σ i = 1 n F i M y + Σ i = 1 n F i · x i M x - Σ i = 1 n F i · y i
Wherein,I.e. need the error of distribution, a0、a1、a2I.e. Second design factor.
Step S216: for each finite element point, foundation the second design factor, the first load and finite element point are at aerofoil On coordinate, determine the second load that finite element point is corresponding.
A kind of preferably for each finite element point, foundation the second design factor, the first load and finite element point are at the wing Coordinate on face, determines that the mode of the second load that finite element point is corresponding is as follows:
The second load that finite element point is corresponding: F is determined by below equationx=Fx+Fx×(a0+a1×Xx+a2×Yx)；Its In, x is positive integer variable, FxFor the first load of i-th finite element point, XxIt isxThe abscissa of i finite element point, YxIt is The vertical coordinate of x finite element point, a0、a1、a2It it is the second design factor.
Step S218: the second load determined is carried out with finite element point corresponding storage, and generates the text of specific format.
Setting for specific format can be configured according to the actual requirements by those skilled in the art, and the present invention implements This is not especially limited by example, such as, is arranged to the form of Force card, Excel tableau format etc..
The determination plane airfoil load location mode provided by the embodiment of the present invention, by the aerodynamic loading on testing site certainly Dynamic be assigned on finite element point, be to consider according to finite element node coordinate position, therefore have the strongest practicality, with And reasonability.Moreover, the distribution scheme that the embodiment of the present invention provides, owing to being automatically to be entered aerodynamic loading by calculating equipment Row distribution, and without participating in manually, therefore, the accuracy of result of calculation is high.Another further aspect, is calculating each finite element point After the load of upper distribution, determine distribution error according to total input load, according to distribution error to the load of distribution on each finite point It is modified, it is possible to the pressure realizing distributing always carries and always carries with input pressure equal and press heart position identical, thus ensures pneumatic The reasonability of load distribution.
Embodiment three
With reference to Fig. 6, it is shown that a kind of structured flowchart determining plane airfoil load distribution unit of the embodiment of the present invention three.
The determination plane airfoil load distribution unit of the embodiment of the present invention comprises determining that module 502, is used for determining to be calculated Each finite element point of comprising of plane airfoil；Acquisition module 504, for obtain coordinate that on described aerofoil, each testing site is corresponding with And CP value；First coefficient determination module 506, determines the first calculating system for the coordinate corresponding according to each testing site and CP value Number；First load determines module 508, for being respectively arranged with on described aerofoil according to setting regular calculating according to described first design factor The first load that limit unit point is corresponding；Error determination module 510, for described in the first LOAD FOR corresponding according to each finite element point The full payload of aerofoil, and described full payload is compared with total input load, determine distribution error；Second coefficient determination module 512, for first load corresponding according to described distribution error, each finite element point and each finite element point coordinate on aerofoil Determine the second design factor；Second load determines module 514, for for each finite element point, according to the second design factor, the One load and finite element point coordinate on aerofoil, determine the second load that finite element point is corresponding.
By the device of the determination plane airfoil load distribution that the embodiment of the present invention provides, by the aerodynamic loading on testing site Be automatically assigned on finite element point, be to consider according to finite element node coordinate position, therefore have the strongest practicality, And reasonability.Moreover, the distribution scheme that the embodiment of the present invention provides, owing to being automatically to aerodynamic loading by calculating equipment It is distributed, and without participating in manually, therefore, the accuracy of result of calculation is high.Another further aspect, is calculating each finite element On point after the load of distribution, determine distribution error according to total input load, according to distribution error to the load of distribution on each finite point Lotus is modified, it is possible to the pressure realizing distributing always carries and always carries with input pressure equal and press heart position identical, thus ensures gas The reasonability of dynamic load distribution.
Embodiment four
With reference to Fig. 7, it is shown that a kind of structured flowchart determining plane airfoil load distribution unit of the embodiment of the present invention four.
The embodiment of the present invention is the further optimization to the determination plane airfoil load distribution unit in embodiment three, optimizes After device comprise determining that module 602, for determining each finite element point that plane airfoil to be calculated comprises；Acquisition module 604, for obtaining the coordinate and CP value that on described aerofoil, each testing site is corresponding；First coefficient determination module 606, for foundation Coordinate and CP value that each testing site is corresponding determine the first design factor；First load determines module 608, for according to described the One design factor calculates, according to setting rule, the first load that on described aerofoil, each finite element point is corresponding；Error determination module 610, For the full payload of aerofoil described in the first LOAD FOR corresponding according to each finite element point, and by described full payload with always input load Lotus compares, and determines distribution error；Second coefficient determination module 612, for according to described distribution error, each finite element point pair The first load and each finite element point coordinate on aerofoil answered determine the second design factor；Second load determines module 614, For for each finite element point, according to the second design factor, the first load and finite element point coordinate on aerofoil, determining The second load that finite element point is corresponding.
Preferably, described first coefficient determination module 606 includes: the first submodule 6061, for according to each testing site Coordinate and the first design factor build the first matrix；Second submodule 6062, for the CP value structure corresponding according to each testing site Build the second matrix；3rd submodule 6063, for determining the 3rd matrix by the first matrix and the second matrix；4th submodule 6064, each matrix element in the 3rd matrix is defined as the first design factor.
Preferably, described first load determines that module 608 includes: packet submodule 6081, for by described aerofoil Finite element point is grouped according to FEM (finite element) model；Load determines submodule 6082, for each for often organize in finite element point Finite element point determines the first load of correspondence according to setting rule.
Preferably, load determines that submodule 6082 is true according to setting rule for each finite element point often organizing in finite element point When determining the first corresponding load: determine the cell type of unit associated by current group finite element point；Current group finite element point is closed When the cell type of receipts or other documents in duplicate unit is tetragon, tetragon is diagonally divided into four trianglees；Calculate each triangle respectively The testing site separate loading that the finite element point of apex is corresponding；For each finite element point, according to the testing site that finite element point is corresponding Separate loading, acceleration of gravity and ram compression coefficient determine the first load.
Preferably, described second load determine module 614 for each finite element point, according to the second design factor, first Load and finite element point coordinate on aerofoil, when determining the second load corresponding to finite element point: determined by below equation The second load that finite element point is corresponding: determine the second load that finite element point is corresponding: F by below equationX=FX+FX×(a0+a1 ×XX+a2×YX)；Wherein, X is positive integer variable, FXFor the first load of x-th finite element point, XXFor i-th finite element point Abscissa, YXFor the vertical coordinate of x-th finite element point, a0、a1、a2It it is the second design factor.
Preferably, described device also includes: text generation module, for determining that module is at described pin in described second load To each finite element point, according to the second design factor, the first load and finite element point coordinate on aerofoil, determine finite element After the second load that point is corresponding, the second load determined is carried out with finite element point corresponding storage, and generates specific format Text.
The device of the determination plane airfoil load distribution of the present embodiment is used for realizing previous embodiment one and embodiment two In determine the method that plane airfoil load is distributed accordingly, and there is the beneficial effect of corresponding embodiment of the method, at this not Repeat again.
Determine provided herein scheme that plane airfoil load is distributed not with any certain computer, virtual system or its Its equipment is intrinsic relevant.Various general-purpose systems can also be used together with based on teaching in this.As described above, structure There is the structure required by the system of the present invention program be apparent from.Additionally, the present invention is also not for any certain programmed Language.It is understood that, it is possible to use various programming languages realize the content of invention described herein, and above to specific language The description that speech is done is the preferred forms in order to disclose the present invention.
In description mentioned herein, illustrate a large amount of detail.It is to be appreciated, however, that the enforcement of the present invention Example can be put into practice in the case of not having these details.In some instances, it is not shown specifically known method, structure And technology, in order to do not obscure the understanding of this description.
Similarly, it will be appreciated that one or more in order to simplify that the disclosure helping understands in each inventive aspect, exist Above in the description of the exemplary embodiment of the present invention, each feature of the present invention is grouped together into single enforcement sometimes In example, figure or descriptions thereof.But, the method for the disclosure should not be construed to reflect an intention that i.e. required guarantor The application claims feature more more than the feature being expressly recited in each claim protected.More precisely, such as right As claim is reflected, inventive aspect is all features less than single embodiment disclosed above.Therefore, it then follows tool Claims of body embodiment are thus expressly incorporated in this detailed description of the invention, the conduct of the most each claim itself The independent embodiment of the present invention.
Those skilled in the art are appreciated that and can carry out the module in the equipment in embodiment adaptively Change and they are arranged in one or more equipment different from this embodiment.Can be the module in embodiment or list Unit or assembly are combined into a module or unit or assembly, and can put them in addition multiple submodule or subelement or Sub-component.In addition at least some in such feature and/or process or unit excludes each other, can use any Combine all features disclosed in this specification (including adjoint claim, summary and accompanying drawing) and so disclosed appoint Where method or all processes of equipment or unit are combined.Unless expressly stated otherwise, this specification (includes adjoint power Profit requires, summary and accompanying drawing) disclosed in each feature can be carried out generation by providing identical, equivalent or the alternative features of similar purpose Replace.
Although additionally, it will be appreciated by those of skill in the art that embodiments more described herein include other embodiments Some feature included by rather than further feature, but the combination of the feature of different embodiment means to be in the present invention's Within the scope of and form different embodiments.Such as, in detail in the claims, embodiment required for protection one of arbitrarily Can mode use in any combination.
The all parts embodiment of the present invention can realize with hardware, or to run on one or more processor Software module realize, or with combinations thereof realize.It will be understood by those of skill in the art that and can use in practice Microprocessor or digital signal processor (DSP) realize determination plane airfoil load distribution according to embodiments of the present invention The some or all functions of the some or all parts in scheme.The present invention is also implemented as being retouched here for execution Part or all equipment of the method stated or device program (such as, computer program and computer program). The program of such present invention of realization can store on a computer-readable medium, or can have one or more signal Form.Such signal can be downloaded from internet website and obtain, or on carrier signal provide, or with any its He provides form.
The present invention will be described rather than limits the invention to it should be noted above-described embodiment, and ability Field technique personnel can design alternative embodiment without departing from the scope of the appended claims.In the claims, Any reference marks that should not will be located between bracket is configured to limitations on claims.Word " comprises " and does not excludes the presence of not Arrange element in the claims or step.Word "a" or "an" before being positioned at element does not excludes the presence of multiple such Element.The present invention and can come real by means of including the hardware of some different elements by means of properly programmed computer Existing.If in the unit claim listing equipment for drying, several in these devices can be by same hardware branch Specifically embody.Word first, second and third use do not indicate that any order.These word explanations can be run after fame Claim.

Claims (12)

1. the method determining that plane airfoil load is distributed, it is characterised in that including:
Determine each finite element point that plane airfoil to be calculated comprises；
Obtain coordinate and CP value that on described aerofoil, each testing site is corresponding；
The coordinate corresponding according to each testing site and CP value determine the first design factor；
Calculate, according to setting rule, the first load that on described aerofoil, each finite element point is corresponding according to described first design factor；
According to the full payload of aerofoil described in the first LOAD FOR that each finite element point is corresponding, and by described full payload with always input load Lotus compares, and determines distribution error；
First load corresponding according to described distribution error, each finite element point and each finite element point coordinate on aerofoil determine Second design factor；
For each finite element point, according to the second design factor, the first load and finite element point coordinate on aerofoil, determine The second load that finite element point is corresponding.
Method the most according to claim 1, it is characterised in that the described coordinate corresponding according to each testing site and CP value are true The step of fixed first design factor includes:
Coordinate and the first design factor according to each testing site build the first matrix；
The CP value corresponding according to each testing site builds the second matrix；
The 3rd matrix is determined by the first matrix and the second matrix；
Each matrix element in 3rd matrix is defined as the first design factor.
Method the most according to claim 1, it is characterised in that described regular according to setting according to described first design factor Calculate the step of the first load that each finite element point is corresponding on described aerofoil to include:
Finite element point on described aerofoil is grouped according to FEM (finite element) model；
The first corresponding load is determined according to setting rule for each finite element point often organized in finite element point.
Method the most according to claim 3, it is characterised in that for each finite element point often organized in finite element point according to setting Set pattern then determines that the step of the first load of correspondence includes:
Determine the cell type of unit associated by current group finite element point；
When the cell type of unit is tetragon associated by current group finite element point, tetragon is diagonally divided into four three Dihedral；
Calculate the testing site separate loading that the finite element point at each triangular apex is corresponding respectively；
For each finite element point, testing site separate loading, acceleration of gravity and the ram compression coefficient corresponding according to finite element point are true Fixed first load.
Method the most according to claim 1, it is characterised in that for each finite element point, according to the second design factor, the One load and finite element point coordinate on aerofoil, determine that the step of the second load that finite element point is corresponding includes:
The second load that finite element point is corresponding: F is determined by below equationx=Fx+Fx×(a0+a1×Xx+a2×Yx)；
Wherein, x is positive integer variable, FxFor the first load of x-th finite element point, XxFor the abscissa of x-th finite element point, YxFor the vertical coordinate of x-th finite element point, a0、a1、a2It it is the second design factor.
Method the most according to claim 1, it is characterised in that described for each finite element point, calculate according to second Coefficient, the first load and finite element point coordinate on aerofoil, after determining the step of the second load that finite element point is corresponding, Described method also includes:
The second load determined is carried out with finite element point corresponding storage, and generates the text of specific format.
7. the device determining that plane airfoil load is distributed, it is characterised in that including:
Determine module, for determining each finite element point that plane airfoil to be calculated comprises；
Acquisition module, for obtaining the coordinate and CP value that on described aerofoil, each testing site is corresponding；
First coefficient determination module, determines the first design factor for the coordinate corresponding according to each testing site and CP value；
First load determines module, for calculating on described aerofoil each limited according to described first design factor according to setting rule The first load that unit's point is corresponding；
Error determination module, for the full payload of aerofoil described in the first LOAD FOR corresponding according to each finite element point, and by institute State full payload to compare with total input load, determine distribution error；
Second coefficient determination module, for first load corresponding according to described distribution error, each finite element point and each limited Unit's point coordinate on aerofoil determines the second design factor；
Second load determines module, for for each finite element point, according to the second design factor, the first load and finite element Point coordinate on aerofoil, determines the second load that finite element point is corresponding.
Device the most according to claim 7, it is characterised in that described first coefficient determination module includes:
First submodule, for building the first matrix according to coordinate and first design factor of each testing site；
Second submodule, builds the second matrix for the CP value corresponding according to each testing site；
3rd submodule, for determining the 3rd matrix by the first matrix and the second matrix；
4th submodule, each matrix element in the 3rd matrix is defined as the first design factor.
Device the most according to claim 7, it is characterised in that described first load determines that module includes:
Packet submodule, for being grouped the finite element point on described aerofoil according to FEM (finite element) model；
Load determines submodule, for determining the of correspondence for each finite element point often organized in finite element point according to setting rule One load.
Device the most according to claim 9, it is characterised in that load determines that submodule is for often organizing in finite element point Each finite element point is according to when setting regular the first load determining correspondence:
Determine the cell type of unit associated by current group finite element point；
When the cell type of unit is tetragon associated by current group finite element point, tetragon is diagonally divided into four three Dihedral；
Calculate the testing site separate loading that the finite element point at each triangular apex is corresponding respectively；
For each finite element point, testing site separate loading, acceleration of gravity and the ram compression coefficient corresponding according to finite element point are true Fixed first load.
11. devices according to claim 7, it is characterised in that described second load determines that module is for each finite element Point, according to the second design factor, the first load and finite element point coordinate on aerofoil, determine that finite element point is corresponding second During load:
The second load that finite element point is corresponding: F is determined by below equationx=Fx+Fx×(a0+a1×Xx+a2×Yx)；
Wherein, x is positive integer variable, FxFor the first load of x-th finite element point, XxFor the abscissa of x-th finite element point, YxFor the vertical coordinate of i-th finite element point, a0、a1、a2It it is the second design factor.
12. devices according to claim 7, it is characterised in that described device also includes:
Text generation module, for described second load determine module described for each finite element point, according to the second meter Calculate coefficient, the first load and finite element point coordinate on aerofoil, after determining the second load that finite element point is corresponding, will really The second fixed load carries out corresponding storage with finite element point, and generates the text of specific format.
CN201610211106.5A 2016-04-06 2016-04-06 A kind of method and apparatus of determining plane airfoil load distribution Withdrawn - After Issue CN105912762B (en)

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CN107016218B (en) * 2017-05-02 2020-12-04 西安合科软件有限公司 Method and device for determining finite element point load distribution in wingtip winglet of airplane
CN107016218A (en) * 2017-05-02 2017-08-04 西安合科软件有限公司 A kind of method and apparatus for determining that finite element point load is distributed in airplane wingtip winglet aerofoil
CN107273638A (en) * 2017-07-06 2017-10-20 中国航空工业集团公司西安飞机设计研究所 A kind of fuselage based on horizontal tail load and empennage connecting hinge point load distribution method
CN109323841B (en) * 2018-11-23 2020-03-13 中国航空工业集团公司沈阳飞机设计研究所 Coordination method for total load and distributed load of wing based on grid
CN109323841A (en) * 2018-11-23 2019-02-12 中国航空工业集团公司沈阳飞机设计研究所 The coordination approach of wing load and distributed load based on grid
CN109684674A (en) * 2018-12-04 2019-04-26 中国航空工业集团公司西安飞机设计研究所 A kind of hatch door aerodynamic loading processing method
CN109684674B (en) * 2018-12-04 2023-05-05 中国航空工业集团公司西安飞机设计研究所 Cabin door pneumatic load processing method
CN111339605A (en) * 2018-12-18 2020-06-26 株式会社斯巴鲁 Load calculation device and aircraft
CN111339605B (en) * 2018-12-18 2024-05-03 株式会社斯巴鲁 Load calculation device and aircraft

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