CN102221444B - Device for adjusting wing surface of wing wind tunnel blowing model and adjustment method - Google Patents

Abstract

The invention relates to a device for adjusting the wing surface of a wing wind tunnel blowing model and an adjustment method. In the device provided by the invention, the width of a support base is equal to the chordwise length of the wing wind tunnel blowing model; the length of the support base is equal to the spanwise length of the wing wind tunnel blowing model; multiple rows of actuators are distributed along the length direction of the support base; each row of actuators comprises multiple actuators; each actuator is respectively positioned on each design point of the wing and corresponds to the horizontal ordinates of each design point of the wing; the actuators are installed on the upper surface and lower surface of the support base in pairs; and the actuators in the same column on the same surface are connected through a data line and used for receiving the same control signals and carrying out the equal amplitude displacement. The invention provides a convenient and practical wing surface deformation adjusting mechanism for the wing surface deformation based on the wing shape design of a wind tunnel experiment, establishes a high-efficiency wing shape optimization design system by means of the environment and conditions of the wind tunnel experiment and provides different wing shape results for the engineering actually, thereby improving the design level and design efficiency of the existing wing shape.

Description

A kind of device and method of adjustment of adjusting wing blasting model wing surface

Technical field

The present invention relates to the experimental technique field in the modern aerospace field, specifically is a kind of device and method of adjustment of adjusting wing blasting model wing surface.

Background technology

Aerofoil profile refers to the cross-sectional profile of aircraft wing, wing is the main lift member of aircraft, the flat shape of wing is determined by the weight of aircraft flight speed and aircraft basically, after in case the flat shape of wing is established, the performance quality of wing depends on the aerodynamic performance of aerofoil profile fully, so aerofoil profile is the fundamental that aerospace field is constantly studied for a long time.

Just because of the special value of aerofoil profile, since the thirties in last century, the U.S. just develops famous NACA4 figure place, 5 figure places series aerofoil profile and 6 serial aerofoil profiles etc.Aviation advanced countries such as USSR (Union of Soviet Socialist Republics), Germany, France, Britain have all set up the profile set of oneself.Along with the raising of air speed, supercritical airfoil, high speed laminar flow airfoil etc. have been developed in the world again in succession.In addition, the Airfoil Design technology also has the blade in extremely important value such as the wind-driven generator, the propeller section in the thrust power etc. in other field.Yet, along with the development in fields such as Aero-Space, because the difference of task can not simply adopt existing certain aerofoil profile in concrete engineering design, but need be in the basic enterprising one-step optimization design of advancing of original certain aerofoil profile.Along with the raising of Fluid Mechanics Computation (CFD) technology, in recent years, the method for using the CFD technology to carry out Airfoil Design is developed fast.Relying on CFD to carry out in the method for Airfoil Design, types such as anti-method for designing and Optimization Design are arranged, and method for designing is also more and more meticulousr with the CFD technology that adopts, if Beoyin747 wing design studies process is again being found to the design that becomes more meticulous of its different section shapes as American scholar Jameson professor, the wing resistance can reduce 3-5% even higher, however the variable quantity of wing profile (δ=10 within its aerofoil surface boundary layer thickness scope only ^-3～10 ^-2Magnitude).As seen, the design of aerofoil profile is very meticulous and responsive.

Though the method that relies on CFD to carry out Airfoil Design is rapidly developed, but still have following problems: (1) is as the aerofoil profile Optimization Design, especially adopt the Airfoil Design method of global optimization approach, often need to carry out a large amount of aerofoil profile flow field computings, according to relevant document introduction, the optimal design of an aerofoil profile profile may need to reach several thousand times Flow Field Calculation.And the calculated amount of finding the solution aerodynamics fundamental equation (Navier-Stokes equation) is very big, and owing to this reason, people still adopt approximate flow field analysis method, but the loss that brings precision, thereby influences the designing quality of aerofoil profile.(2) even do not consider the huge calculated amount of CFD, level with present CFD, because the theoretical question of turbulent flow itself does not solve, laminar flow changes the factor of twisting to turbulent flow and has very big uncertainty, even so adopt best CFD software at present, can not guarantee to design the most reliable outstanding aerofoil profile.

For these reasons, develop existing actual application value, have high efficiency Airfoil Design system simultaneously the contemporary aircraft Airfoil Design had important value.And a cover can be accepted programmed instruction in this design system, and the gordian technique that structure just becomes this system is adjusted in the airfoil surface distortion of timely high-precision adjustment air foil shape.And existing wing deformation technology can not be realized particular location point microdeformation, can not be efficiently control by computing machine realize Airfoil Design continuously, be difficult to satisfy the demand of optimal design.

Summary of the invention

Carry out the huge calculated amount of aerofoil profile optimal design, the restriction that the while is also avoided the development level of present CFD own for fear of present dependence CFD technology, the present invention proposes a kind of device and method of adjustment of adjusting wing blasting model wing surface.

The present invention includes supporting mechanism and control gear.Wherein the pedestal in the supporting mechanism is tabular, the tangential equal in length of its width and wing blasting model, and its length is identical to length with the exhibition of wing blasting model.Actuator in the supporting mechanism has many rows, be distributed on the pedestal along the pedestal length direction, and first row's actuator is positioned at 16.7% place of pedestal length, and last row's actuator is positioned at 83.3% place of pedestal length.Every row's actuator is made up of a plurality of actuator; The horizontal ordinate of each the actuator position on the same row is that actuator is identical with the horizontal ordinate of Airfoil Design point along the distributing position on the base width direction.Described actuator is mounted in pairs in upper surface and the lower surface of pedestal; The a plurality of actuator that are in same row on the same surface link together by a data lines, are used for accepting same control signal and making the constant amplitude displacement.

Control gear comprises center-controlling computer, piezoelectric type actuator controller and aerodynamic balance.The aerodynamic balance that is positioned at the wing model skin-surface is transferred to center-controlling computer by data line with flow field data message D3; Center-controlling computer transfers to the piezoelectric type actuator controller with the deflection of determining by steering order D1; The piezoelectric type actuator controller is electric signal D2 with the instruction transformation that receives, and is transferred to each actuator in the supporting mechanism; Each actuator is according to the height of each the self-adjusting mobile terminal of deflection signal that receives, and then realizes adjustment to wing model skin-surface height by the support bar of the bracing frame that is connected with each actuator mobile terminal, thereby realization is to the adjustment of aerofoil; Each actuator is done the constant amplitude displacement along the wing model exhibition to each actuator of arranging when action.

The quantity of described bracing frame is identical with the quantity of actuator on each row; Bracing frame is formed by supporting traverse with the orthogonal a plurality of support bars of supporting traverse; The exhibition appearance of the length of supporting traverse and wing together; The length of a plurality of support bars is identical, and the position of every row actuator mounting hole is corresponding on the position of each support bar and the pedestal; One end of support bar is the external thread external thread rod in the same way with the actuator mobile terminal; The bar footpath of support bar is identical with the external diameter of actuator mobile terminal.

Described sleeve is inner thread sleeve, by this sleeve the mobile terminal of actuator and the support bar of bracing frame is linked together.Described wing model covering covers on the supporting traverse of bracing frame, realizes adjustment to the wing cover surface configuration by the height of adjusting each support bar in the bracing frame, to obtain the wing model of different aerofoil profiles.

The horizontal ordinate of the position of every row's actuator mounting hole is identical with the horizontal ordinate of the Airfoil Design point of this place's upper surface of the airfoil; The quantity of every row's actuator mounting hole is counted identical with the design point of this place's upper surface of the airfoil.

The invention allows for a kind of wing blasting model wing surface method of adjustment, its concrete steps are:

Step 1 is determined target lift L according to designing requirement ₀The initial aerofoil profile of aerofoil adjusting mechanism is set, obtains the initial displacement amount S of each row actuator ₁, S ₂..., S _a, wherein a is the quantity of Airfoil Design point; To the experiment of drying of the empirical model of initial aerofoil profile, obtain each row actuator the lift c at corresponding design point place _0l1, c _0l2..., c _0lbWith each row actuator the lift c at corresponding application point place _0l1, c _0l2..., c _0lbBe transferred to center-controlling computer, obtain the lift of initial aerofoil profile

Each row actuator the corresponding application point b that counts identical with the quantity of Airfoil Design point.The lift L of storing initial aerofoil profile and actuator initial displacement amount S ₁, S ₂..., S _a, wherein a is identical with the quantity of Airfoil Design point.

Step 2 provides population S1 at random, and the individuality that this population S1 comprises is the displacement variable Δ S of each row actuator of aerofoil adjusting mechanism ₁, Δ S ₂... Δ S _c, wherein c is identical with the quantity of Airfoil Design point, puts genetic iteration time counter t=1 simultaneously; The S1 displacement variable of population is transferred to center-controlling computer.

Step 3, center-controlling computer is respectively organized actuator with the displacement variable data message that obtains by what actuator controller was transferred to the aerofoil adjusting mechanism, each is organized actuator and makes corresponding displacement adjustment according to after the change in displacement information that receives, and obtains new airfoil shape.

Step 4 is to the experiment of drying of wing blasting model; Aerodynamic balance measure empirical model respectively organize actuator the lift c at corresponding application point place _L1, c _L2..., c _Lm, wherein m is identical with the quantity of Airfoil Design point; Give center-controlling computer with this lift data information transfer.

Step 5, by center-controlling computer calculate respectively organize actuator the lift summation at corresponding application point place

And will Compare with the lift L of aerofoil profile, if

Be not less than lift L, obtain current lift Storage L also stores population S1 in storage unit S; Compare L and target lift L ₀Size, if L is not less than L ₀, then program stops, and be met the aerofoil profile of target lift requirement, and current aerofoil profile is the aerofoil profile that satisfies the requirement of target lift; If L is less than L ₀, the size between the largest optimization iterations T=100 of count value t and setting in the counter relatively, if t less than T then proceed heredity and calculate, otherwise program termination.When largest optimization iterations T that count value t in the counter equals to set, be that count value t and largest optimization iterations T are at 100 o'clock in the counter, displacement variable is exactly to the required displacement variable of maximum lift aerofoil profile by initial aerofoil profile among the storage unit S.

Step 6 is passed through formula

$p\left(i\right)=\frac{c_{\mathrm{li}}}{\underset{j=1}{\overset{m}{\mathrm{\Σ}}}{c}_{\mathrm{lj}}},(1\≤i\≤m)$

Determine each individual Δ s among the population S1 _iCorresponding selection Probability p (i); And utilize formula according to the selection Probability p (i) that obtains

$q\left(i\right)=\underset{j=1}{\overset{i}{\mathrm{\Σ}}}p\left(i\right),(1\≤i\≤m)$

Determine each individual Δ s _iCorresponding cumulative probability q (i); In [0,1] interval, produce equally distributed random number r at random ₁, r ₂..., r _n, wherein n is identical with the quantity of Airfoil Design point; If r _i≤ q (1) then chooses first the individual Δ s among the population S1 _iAs the new S ' of colony ₁If one of them individuality is q (k-1)≤r _i≤ q (k), (2≤k≤m, 2≤i≤n) then choose k individual Δ s _kAs the new S ' of colony ₁One of them individuality; With random number r ₁, r ₂..., r _nRelatively form the new S ' of colony with cumulative probability q (i) one by one ₁The described quantity that produces equally distributed random number in [0,1] interval at random is consistent with the quantity of wing blasting Model Design point; The described S ' of colony ₁All the quantity with wing blasting model is identical for middle individual quantity.

Step 7 is to the S ' of colony that obtains ₁In individuality carry out random pair; With back eight in the sixteen bit binary code of the displacement variable of intercoursing this individuality representative of expression between a pair of individuality, thereby form new individuality, and new individually replace former individual new population S2, i.e. the displacement variable Δ s of the actuator of aerofoil adjusting mechanism of forming with what produce " ₁, Δ s " ₂..., Δ s " _p, wherein p is identical with the quantity of Airfoil Design point;

Step 8 as population of new generation, namely replaces S1 with S2 with the S2 of colony, counter t=t+1, and repeating step 3 is to step 8, until the requirement of satisfying step 5.

The present invention is that the appearance profile with basic aerofoil profile is based upon on the support system that can regulate, this support system is made up of a plurality of support adapter, each regulator can stretch, telescopic variation by each regulator, reach the purpose that changes the aerofoil profile profile, whole support system and aerofoil profile have constituted wind tunnel experiment blowing model together.

All regulators of aerofoil adjusting mechanism of the present invention and the measuring sensor of aerofoil profile aeroperformance are connected with the center optimizing computer.Handle the aerofoil profile aerodynamic data that the reception measuring sensor transmits by genetic algorithm, then according to the changes in aerodynamic forces of balance measurement, optimize software and assign the stroke that each regulator is adjusted in instruction for each regulator, go out the stroke of each regulator like this by the method final optimization pass of heredity of many generations; This Optimization design principle is with at present identical based on the optimization algorithm of CFD technology, different is: need constantly call CFD software based on the aerofoil profile optimal design system of CFD technology at present and carry out Field Flow Numerical Simulation acquisition airfoil aerodynamic performances, and the present invention directly directly adjusts the optimal design of carrying out by flow field and the aerofoil profile aerodynamic force measurement data of wind tunnel experiment to aerofoil.

Thereby the aerofoil distortion that the present invention needs for the Airfoil Design based on wind tunnel experiment provides a kind of aerofoil distortion adjusting mechanism of high-efficiency high-accuracy to eliminate carries out the problem that a large amount of CFD calculate the optimization inefficiency of bringing when present dependence CFD technology is carried out Airfoil Design; Simultaneously, the theoretical defects of CFD technology in calculating aerofoil profile VISCOUS FLOW process, the problems such as uncertainty of computing method have been eliminated.Airfoil Design result's reliability physically and engineering practicability have been guaranteed.

From the efficient aspect relatively, under present computing machine condition, the time of calculating a viscosity aerofoil profile flow field needs 1 hour basically, and one second kind is just passable basically the time that obtains a flow field in the wind tunnel experiment, so the optimal design efficient of aerofoil deformation mechanism provided by the present invention and corresponding with it Optimization Design based on wind tunnel experiment is to utilize 3600 times of CFD design efficiency basically.From the precision aspect, wind tunnel experiment is that reproduce in the laboratory of true aerofoil profile condition of work basically, and its error only is that wind tunnel wall disturbs and the error of platform measuring; And the Flow Field Calculation precision of dependence CFD still can not be demarcated at present fully, and theoretically, just there is theoretic uncertainty in the method itself that relies on turbulence model to calculate VISCOUS FLOW at present.So it is reliable more than the technological approaches that relies on the CFD design that aerofoil adjusting mechanism proposed by the invention and the aerofoil profile of Optimization Design are optimized precision.

The present invention is used for the modern aerospace field, can improve present Airfoil Design level and design efficiency, rely on wind tunnel experiment environment and condition, by being deformation mechanism with Airfoil Design, set up practical, aerofoil profile optimal design system efficiently, different aerofoil profile results is provided for engineering is actual.

Description of drawings

Fig. 1 is the schematic layout pattern in adjusting mechanism and the wing;

Fig. 2 is the partial schematic diagram of adjusting mechanism;

Fig. 3 is the structural representation of adjusting mechanism;

Fig. 4 is the structural representation of supporting base, and wherein a is vertical view, and b is left view;

Fig. 5 is the structural representation of bracing frame;

Fig. 6 is the control flow synoptic diagram of control gear.Wherein:

1. supporting base 2. elasticity coverings 3. bracing frames 4. coupling sleeves 5. actuator

6. coupling bolt 7. center-controlling computer 8. piezoelectric type actuator controllers 9. supporting mechanisms

10. aerodynamic balance D1. steering order D2. electric signal D3. flow field information

Embodiment

Embodiment one

Present embodiment is a kind of aerofoil distortion adjusting gear of the wing blasting model for Airfoil Design, wing blasting model adopts the NACA0012 aerofoil profile as initial aerofoil profile, and wing blasting model perpendicular to exhibition to each cross section on the chord length of NACA0012 aerofoil profile identical.Described wing blasting model Airfoil Design point is 34, is divided into two groups in same wing section along tangential upper surface and the lower surface that is distributed in wing of aerofoil profile, and upper surface is identical with the horizontal ordinate of the design point of the mutual correspondence of lower surface.The initial point of coordinate system is positioned at wing blasting model leading edge midpoint in the present embodiment, abscissa axis is tangential from the leading edge to the trailing edge along wing blasting model, axis of ordinates along the exhibition of wing blasting model to from the model root to taper, the Z axle makes progress perpendicular to XOY plane.

Present embodiment comprises supporting mechanism 9 and control gear.Wherein supporting mechanism 9 is made up of supporting base 1, elasticity covering 2, bracing frame 3, coupling sleeve 4 and actuator 5 and coupling bolt 6; Control gear comprises center-controlling computer 7, piezoelectric type actuator controller 8 and aerodynamic balance 10.

Wing model in the present embodiment is used for carrying out Airfoil Design, is to equate with a kind of aerofoil profile and their chord length along the tangential cross section aerofoil profile of wing blasting model.Supporting base 1 in the supporting mechanism 9 is tabular, the tangential equal in length of its width and wing blasting model, and its length is identical to length with the exhibition of wing blasting model.Be distributed with the actuator mounting hole on the supporting base 1.This mounting hole is divided into three rows, is distributed in 16.7%, 50% and 83.3% place of wing blasting model length along supporting base 1 length direction.Every row has 17 mounting holes, and the horizontal ordinate of each position of mounting hole is identical with the horizontal ordinate of these 17 design point positions of upper surface of the airfoil, place.17 design point quantity of the quantity of every row's mounting hole and this place's upper surface of the airfoil are identical.

Actuator 5 adopts closed piezoelectric actuator 7VS12, external thread formula mobile terminal.Actuator 5 is mounted in pairs in upper surface and the lower surface of supporting base 1 by being built in coupling bolt in supporting base 1 mounting hole.Three actuator that are in same row on the same surface link together by a data lines, are used for accepting same control signal and making the constant amplitude displacement.

Coupling bolt 6 is double end external thread coupling bolts.The internal diameter of mounting hole is identical on coupling bolt 6 middle part diameters and the supporting base 1; The external diameter at coupling bolt 6 two ends is identical with the internal diameter of the internal thread connecting hole of actuator 5 lower ends.To be positioned at same mounting hole on the supporting base 1 by coupling bolt 6, and a pair of actuator 5 that is in upper surface and lower surface respectively interconnects.

Bracing frame 3 has 34, all makes with aluminium alloy.Bracing frame 3 is formed by supporting traverse with orthogonal three support bars of supporting traverse.The exhibition appearance of the length of supporting traverse and wing together; The length of three support bars is identical, and the position of every row actuator mounting hole is corresponding on the position of each support bar and the supporting base 1.One end of support bar is the external thread external thread rod in the same way with actuator 5 mobile terminals.The bar footpath of support bar is identical with the external diameter of actuator 5 mobile terminals.

Sleeve 4 is inner thread sleeve, and the external diameter of support bar is identical in the external diameter of its internal diameter and actuator 5 mobile terminals and the bracing frame 3.By sleeve 4 mobile terminal of actuator 5 and the support bar of bracing frame 3 are linked together.

In the present embodiment, rubber wing model covering is covered on the supporting traverse of bracing frame 3, realize adjustment to the wing cover surface configuration by the height of adjusting each support bar in the bracing frame 3, to obtain the wing model of different aerofoil profiles.

The control gear of present embodiment comprises center-controlling computer 7, piezoelectric type actuator controller 8 and aerodynamic balance 10, and connects by signal stream between center-controlling computer 7, piezoelectric type actuator controller 8 and the aerodynamic balance 10.Its detailed process is that the data line of actuator 5 is connected with piezoelectric type actuator controller 8 in the supporting mechanism 9; The data line of piezoelectric type actuator controller 8 is connected with center-controlling computer 7; Aerodynamic balance 10 is positioned at the wing model skin-surface position corresponding with Airfoil Design point, and the data line of aerodynamic balance 10 also is connected with center-controlling computer 7.During work, the aerodynamic balance 10 that is positioned at the wing model skin-surface is transferred to center-controlling computer 7 by data line with flow field data message D3; Center-controlling computer 7 transfers to piezoelectric type actuator controller 8 with the deflection of determining by steering order D1.Piezoelectric type actuator controller 8 is electric signal D2 with the instruction transformation that receives, and is transferred to each actuator 5 in the supporting mechanism 9; Each actuator 5 is according to the height of each the self-adjusting mobile terminal of deflection signal that receives, and then realizes adjustment to wing model skin-surface height by the support bar of the bracing frame 3 that is connected with each actuator 5 mobile terminal, thereby realization is to the adjustment of aerofoil.Each actuator 5 is done the constant amplitude displacement along the wing model exhibition to three actuator of arranging when action.

Present embodiment also proposes a kind of aerofoil adjusting mechanism that utilizes and carries out the method for designing that aerofoil profile is optimized, and wing model adopts the NACA0012 aerofoil profile as initial aerofoil profile, and its concrete steps are:

Step 1 is determined target lift L according to designing requirement ₀The initial aerofoil profile of aerofoil adjusting mechanism is set to the NACA0012 aerofoil profile, obtains the displacement s of each row actuator ₁, s ₂..., s ₃₄Open wind-tunnel to the experiment of drying of the empirical model of initial aerofoil profile, aerodynamic balance is measured the 34 row actuator lift c at corresponding application point place separately _0l1, c _0l2..., c _0l34, and give center-controlling computer with this lift data information transfer, calculate the lift under the initial aerofoil profile

And storage L, the displacement s of initial each the row actuator of record ₁, s ₂..., s ₃₄The corresponding position of action point of described 34 row actuator and number are all consistent with position and the number of Airfoil Design (coordinate) point of wing blasting model.

Step 2 provides population S1 at random, and the individuality that this population S1 comprises is the displacement variable Δ s of 34 groups of actuator of aerofoil adjusting mechanism ₁, Δ s ₂..., Δ s ₃₄, put genetic iteration time counter t=1 simultaneously.

Step 3, center-controlling computer is transferred to the displacement variable data message that obtains each row actuator of aerofoil adjusting mechanism by actuator controller, each row actuator is made corresponding displacement adjustment after receiving change in displacement information, change airfoil shape thereby promote support movements.

After step 4, new airfoil shape are adjusted out by adjusting mechanism, open wind-tunnel to the empirical model experiment of drying; Aerodynamic balance measure thereupon each row actuator of empirical model the lift c at corresponding application point place _L1, c _L2... c _L34, and give center-controlling computer with this lift data information transfer.

After step 5, center-controlling computer receive the lift data at application point place, calculate the lift summation at these some places

And will L compares with lift, if

Be not less than lift L, then

And the value of storage L and to store current displacement variable be that population S1 is in storage unit S; Compare L and target lift L ₀Size, if L is not less than L ₀, then program stops, and be met the aerofoil profile of target lift requirement, and current aerofoil profile is the aerofoil profile that satisfies the requirement of target lift; If L is less than L ₀, the size between the largest optimization iterations T=100 of count value t and setting in the counter relatively, if t less than T then proceed heredity and calculate, otherwise program termination.When largest optimization iterations T that count value t in the counter equals to set, be that count value t and largest optimization iterations T are at 100 o'clock in the counter, displacement variable is exactly to the required displacement variable of maximum lift aerofoil profile by initial aerofoil profile among the storage unit S.

Step 6 is passed through formula

$p\left(i\right)=\frac{c_{\mathrm{li}}}{\underset{j=1}{\overset{34}{\mathrm{\Σ}}}{c}_{\mathrm{lj}}},(1\≤i\≤34)$

Determine each corresponding selection Probability p of individual Δ si (i) among the population S1.And utilize formula according to the selection Probability p (i) that obtains

$q\left(i\right)=\underset{j=1}{\overset{i}{\mathrm{\Σ}}}p\left(i\right),(1\≤i\≤34)$

Calculate each individual Δ s _iCorresponding cumulative probability q (i).In [0,1] interval, produce 34 equally distributed random number r at random ₁, r ₂R ₃₄, if ri≤q (1) then chooses first the individual Δ s among the population S1 ₁As the new S ' of colony ₁If one of them individuality is q (k-1)≤r _i≤ q (k), (2≤k≤34,2≤i≤34) then choose k individual Δ s _kAs the new S ' of colony ₁One of them individuality utilizes this method with random number r ₁, r ₂R ₃₄One by one with cumulative probability q (i) thus relatively select 34 and individually form the new S ' of colony ₁

Step 7 is to the S ' of colony that newly obtains ₁In individual Δ s ' ₁, Δ s ' ₂..., Δ s ' ₃₄It is right that random pair produces 17 individualities, with back eight in the sixteen bit binary code of the displacement variable of intercoursing this individuality representative of expression between a pair of individuality, thereby form 34 new individualities, and new individually replace the former individual new population S2 that forms with what produce, namely 34 of the aerofoil adjusting mechanism groups of actuator are with respect to the displacement variable Δ s of initial displacement ₁", Δ s " ₂..., Δ s " ₃₄

Step 8 as population of new generation, namely replaces S1 with S2 with the S2 of colony, counter t=t+1, and repeating step 3 is to step 8, until the requirement of satisfying step 5.

Embodiment two

Present embodiment is a kind of aerofoil distortion adjusting gear of the wing blasting model for Airfoil Design, wing blasting model adopts the NACA0024 aerofoil profile as initial aerofoil profile, and wing blasting model perpendicular to exhibition to each cross section on the chord length of NACA0024 aerofoil profile identical.Described wing blasting model Airfoil Design point is 40, is divided into two groups in same wing section along tangential upper surface and the lower surface that is distributed in wing of aerofoil profile, and upper surface is identical with the horizontal ordinate of the design point of the mutual correspondence of lower surface.The initial point of coordinate system is positioned at wing blasting model leading edge midpoint in the present embodiment, abscissa axis is tangential from the leading edge to the trailing edge along wing blasting model, axis of ordinates along the exhibition of wing blasting model to from the model root to taper, the Z axle makes progress perpendicular to XOY plane.

Present embodiment comprises supporting mechanism 9 and control gear.Wherein supporting mechanism 9 is made up of supporting base 1, elasticity covering 2, bracing frame 3, coupling sleeve 4 and actuator 5 and coupling bolt 6; Control gear comprises center-controlling computer 7, piezoelectric type actuator controller 8 and aerodynamic balance 10.

Wing model in the present embodiment is used for carrying out Airfoil Design, is to equate with a kind of aerofoil profile and their chord length along the tangential cross section aerofoil profile of wing blasting model.Supporting base 1 in the supporting mechanism 9 is tabular, the tangential equal in length of its width and wing blasting model, and its length is identical to length with the exhibition of wing blasting model.Be distributed with the actuator mounting hole on the supporting base 1.This mounting hole is divided into five rows, is distributed in 16.7%, 33.3%, 50%, 66.7% and 83.3% place of wing blasting model length along supporting base 1 length direction.Every row has 20 mounting holes, and the horizontal ordinate of the position of every row's mounting hole is identical with the horizontal ordinate of these 20 design point positions of upper surface of the airfoil, place.20 design point quantity of the quantity of every row's mounting hole and this place's upper surface of the airfoil are identical

Actuator 5 adopts closed piezoelectric actuator 7VS12, external thread formula mobile terminal.Actuator 5 is mounted in pairs in upper surface and the lower surface of supporting base 1 by being built in coupling bolt in supporting base 1 mounting hole.Three actuator that are in same row on the same surface link together by a data lines, are used for accepting same control signal and making the constant amplitude displacement.

Coupling bolt 6 is double end external thread coupling bolts.The internal diameter of mounting hole is identical on coupling bolt 6 middle part diameters and the supporting base 1; The external diameter at coupling bolt 6 two ends is identical with the internal diameter of the internal thread connecting hole of actuator 5 lower ends.To be positioned at same mounting hole on the supporting base 1 by coupling bolt 6, and a pair of actuator 5 that is in upper surface and lower surface respectively interconnects.

Bracing frame 3 has 40, all makes with aluminium alloy.Bracing frame 3 is formed by supporting traverse with orthogonal five support bars of supporting traverse.The exhibition appearance of the length of supporting traverse and wing together; The length of five support bars is identical, and the position of every row actuator mounting hole is corresponding on the position of each support bar and the supporting base 1.One end of support bar is the external thread external thread rod in the same way with actuator 5 mobile terminals.The bar footpath of support bar is identical with the external diameter of actuator 5 mobile terminals.

Sleeve 4 is inner thread sleeve, and the external diameter of support bar is identical in the external diameter of its internal diameter and actuator 5 mobile terminals and the bracing frame 3.By sleeve 4 mobile terminal of actuator 5 and the support bar of bracing frame 3 are linked together.

In the present embodiment, rubber wing model covering is covered on the supporting traverse of bracing frame 3, realize adjustment to the wing cover surface configuration by the height of adjusting each support bar in the bracing frame 3, to obtain the wing model of different aerofoil profiles.

The control gear of present embodiment comprises center-controlling computer 7, piezoelectric type actuator controller 8 and aerodynamic balance 10, and connects by signal stream between center-controlling computer 7, piezoelectric type actuator controller 8 and the aerodynamic balance 10.Its detailed process is that the data line of actuator 5 is connected with piezoelectric type actuator controller 8 in the supporting mechanism 9; The data line of piezoelectric type actuator controller 8 is connected with center-controlling computer 7; Aerodynamic balance 10 is positioned at the wing model skin-surface position corresponding with Airfoil Design point, and the data line of aerodynamic balance 10 also is connected with center-controlling computer 7.During work, the aerodynamic balance 10 that is positioned at the wing model skin-surface is transferred to center-controlling computer 7 by data line with flow field data message D3; Center-controlling computer 7 transfers to piezoelectric type actuator controller 8 with the deflection of determining by steering order D1.Piezoelectric type actuator controller 8 is electric signal D2 with the instruction transformation that receives, and is transferred to each actuator 5 in the supporting mechanism 9; Each actuator 5 is according to the height of each the self-adjusting mobile terminal of deflection signal that receives, and then realizes adjustment to wing model skin-surface height by the support bar of the bracing frame 3 that is connected with each actuator 5 mobile terminal, thereby realization is to the adjustment of aerofoil.Each actuator 5 is done the constant amplitude displacement along the wing model exhibition to five actuator of arranging when action.

Present embodiment also proposes a kind of aerofoil adjusting mechanism that utilizes and carries out the method for designing that aerofoil profile is optimized, and wing model adopts the NACA0024 aerofoil profile as initial aerofoil profile, and its concrete steps are:

Step 1 is determined target lift L according to designing requirement ₀The initial aerofoil profile of aerofoil adjusting mechanism is set to the NACA0024 aerofoil profile, obtains the displacement s of each row actuator ₁, s ₂..., s ₄₀Open wind-tunnel to the experiment of drying of the empirical model of initial aerofoil profile, aerodynamic balance is measured the 40 row actuator lift c at corresponding application point place separately _0l1, c _0l2..., c _0l40, and give center-controlling computer with this lift data information transfer, calculate the lift under the initial aerofoil profile

And storage L, the displacement s of initial each the row actuator of record ₁, s ₂..., s ₄₀The corresponding position of action point of described 40 row actuator and number are all consistent with position and the number of wing blasting Model Design point.

Step 2 provides population S1 at random, and the individuality that this population S1 comprises is the displacement variable Δ s of 40 row actuator of aerofoil adjusting mechanism ₁, Δ s ₂..., Δ s ₄₀, put genetic iteration time counter t=1 simultaneously.

Step 3, center-controlling computer is transferred to the displacement variable data message that obtains each row actuator of aerofoil adjusting mechanism by actuator controller, each row actuator is made corresponding displacement adjustment after receiving change in displacement information, change airfoil shape thereby promote support movements.

After step 4, new airfoil shape are adjusted out by adjusting mechanism, open wind-tunnel to the empirical model experiment of drying; Aerodynamic balance measure thereupon each row actuator of empirical model the lift c at corresponding application point place _L1, c _L2... c _L40, and give center-controlling computer with this lift data information transfer.

After step 5, center-controlling computer receive each lift data of optimizing point, calculate the lift summation at these some places

And will

L compares with lift, if

Be not less than lift L, then

And the value of storage L and to store current displacement variable be that population S1 is in storage unit S; Compare L and target lift L ₀Size, if L is not less than L ₀, then program stops, and be met the aerofoil profile of target lift requirement, and current aerofoil profile is the aerofoil profile that satisfies the requirement of target lift; If L is less than L ₀, the size between the largest optimization iterations T=100 of count value t and setting in the counter relatively, if t less than T then proceed heredity and calculate, otherwise program termination.When largest optimization iterations T that count value t in the counter equals to set, be that count value t and largest optimization iterations T are at 100 o'clock in the counter, displacement variable is exactly to the required displacement variable of maximum lift aerofoil profile by initial aerofoil profile among the storage unit S.

Step 6 is passed through formula

$p\left(i\right)=\frac{c_{\mathrm{li}}}{\underset{j=1}{\overset{40}{\mathrm{\Σ}}}{c}_{\mathrm{lj}}},(1\≤i\≤40)$

Determine each individual Δ s among the population S1 _iCorresponding selection Probability p (i).And utilize formula according to the selection Probability p (i) that obtains

$q\left(i\right)=\underset{j=1}{\overset{i}{\mathrm{\Σ}}}p\left(i\right),(1\≤i\≤40)$

Calculate each individual Δ s _iCorresponding cumulative probability q (i).In [0,1] interval, produce 40 equally distributed random number r at random ₁, r ₂R ₄₀, if r _i≤ q (1) then chooses first the individual Δ s among the population S1 ₁As the new S ' of colony ₁If one of them individuality is q (k-1)≤r _i≤ q (k), (2≤k≤40,2≤i≤40) then choose k individual Δ s _kAs the new S ' of colony ₁One of them individuality utilizes this method with random number r ₁, r ₂R ₄₀One by one with cumulative probability q (i) thus relatively select 40 and individually form the new S ' of colony ₁

Step 7 is to the S ' of colony that newly obtains ₁In individual Δ s ' ₁, Δ s ' ₂..., Δ s ' ₃₄It is right that random pair produces 20 individualities, with back eight in the sixteen bit binary code of the displacement variable of intercoursing this individuality representative of expression between a pair of individuality, thereby form 40 new individualities, and new individually replace the former individual new population S2 that forms with what produce, namely 40 of the aerofoil adjusting mechanism groups of actuator are with respect to the displacement variable Δ s of initial displacement " ₁, Δ s " ₂..., Δ s " ₄₀

Step 8 as population of new generation, namely replaces S1 with S2 with the S2 of colony, counter t=t+1, and repeating step 3 is to step 8, until the requirement of satisfying step 5.

Embodiment three

Present embodiment is a kind of aerofoil distortion adjusting gear of the wing blasting model for Airfoil Design, wing blasting model adopts the NACA2410 aerofoil profile as initial aerofoil profile, and wing blasting model perpendicular to exhibition to each cross section on the chord length of NACA2410 aerofoil profile identical.Described wing blasting model Airfoil Design point is 50, is divided into two groups in same wing section along tangential upper surface and the lower surface that is distributed in wing of aerofoil profile, and upper surface is identical with the horizontal ordinate of the design point of the mutual correspondence of lower surface.The initial point of coordinate system is positioned at wing blasting model leading edge midpoint in the present embodiment, abscissa axis is tangential from the leading edge to the trailing edge along wing blasting model, axis of ordinates along the exhibition of wing blasting model to from the model root to taper, the Z axle makes progress perpendicular to XOY plane.

Present embodiment comprises supporting mechanism 9 and control gear.Wherein supporting mechanism 9 is made up of supporting base 1, elasticity covering 2, bracing frame 3, coupling sleeve 4 and actuator 5 and coupling bolt 6; Control gear comprises center-controlling computer 7, piezoelectric type actuator controller 8 and aerodynamic balance 10.

Wing model in the present embodiment is used for carrying out Airfoil Design, is to equate with a kind of aerofoil profile and their chord length along the tangential cross section aerofoil profile of wing blasting model.Supporting base 1 in the supporting mechanism 9 is tabular, the tangential equal in length of its width and wing blasting model, and its length is identical to length with the exhibition of wing blasting model.Be distributed with the actuator mounting hole on the supporting base 1.This mounting hole is divided into seven rows, is distributed in 16.7%, 27.8%, 38.9%, 50%, 61.1%, 72.2% and 83.3% place of wing blasting model length along supporting base 1 length direction.Every row has 25 mounting holes, and the horizontal ordinate of the position of every row's mounting hole is identical with the horizontal ordinate of these 25 design point positions of upper surface of the airfoil, place.25 design point quantity of the quantity of every row's mounting hole and this place's upper surface of the airfoil are identical

Actuator 5 adopts closed piezoelectric actuator 7VS12, external thread formula mobile terminal.Actuator 5 is mounted in pairs in upper surface and the lower surface of supporting base 1 by being built in coupling bolt in supporting base 1 mounting hole.Three actuator that are in same row on the same surface link together by a data lines, are used for accepting same control signal and making the constant amplitude displacement.

Coupling bolt 6 is double end external thread coupling bolts.The internal diameter of mounting hole is identical on coupling bolt 6 middle part diameters and the supporting base 1; The external diameter at coupling bolt 6 two ends is identical with the internal diameter of the internal thread connecting hole of actuator 5 lower ends.To be positioned at same mounting hole on the supporting base 1 by coupling bolt 6, and a pair of actuator 5 that is in upper surface and lower surface respectively interconnects.

Bracing frame 3 has 50, all makes with aluminium alloy.Bracing frame 3 is formed by supporting traverse with orthogonal seven support bars of supporting traverse.The exhibition appearance of the length of supporting traverse and wing together; The length of seven support bars is identical, and the position of every row actuator mounting hole is corresponding on the position of each support bar and the supporting base 1.One end of support bar is the external thread external thread rod in the same way with actuator 5 mobile terminals.The bar footpath of support bar is identical with the external diameter of actuator 5 mobile terminals.

Sleeve 4 is inner thread sleeve, and the external diameter of support bar is identical in the external diameter of its internal diameter and actuator 5 mobile terminals and the bracing frame 3.By sleeve 4 mobile terminal of actuator 5 and the support bar of bracing frame 3 are linked together.

In the present embodiment, rubber wing model covering is covered on the supporting traverse of bracing frame 3, realize adjustment to the wing cover surface configuration by the height of adjusting each support bar in the bracing frame 3, to obtain the wing model of different aerofoil profiles.

The control gear of present embodiment comprises center-controlling computer 7, piezoelectric type actuator controller 8 and aerodynamic balance 10, and connects by signal stream between center-controlling computer 7, piezoelectric type actuator controller 8 and the aerodynamic balance 10.Its detailed process is that the data line of actuator 5 is connected with piezoelectric type actuator controller 8 in the supporting mechanism 9; The data line of piezoelectric type actuator controller 8 is connected with center-controlling computer 7; Aerodynamic balance 10 is positioned at the wing model skin-surface position corresponding with Airfoil Design point, and the data line of aerodynamic balance 10 also is connected with center-controlling computer 7.During work, the aerodynamic balance 10 that is positioned at the wing model skin-surface is transferred to center-controlling computer 7 by data line with flow field data message D3; Center-controlling computer 7 transfers to piezoelectric type actuator controller 8 with the deflection of determining by steering order D1.Piezoelectric type actuator controller 8 is electric signal D2 with the instruction transformation that receives, and is transferred to each actuator 5 in the supporting mechanism 9; Each actuator 5 is according to the height of each the self-adjusting mobile terminal of deflection signal that receives, and then realizes adjustment to wing model skin-surface height by the support bar of the bracing frame 3 that is connected with each actuator 5 mobile terminal, thereby realization is to the adjustment of aerofoil.Each actuator 5 is done the constant amplitude displacement along the wing model exhibition to seven actuator of arranging when action.

Present embodiment also proposes a kind of aerofoil adjusting mechanism that utilizes and carries out the method for designing that aerofoil profile is optimized, and wing model adopts the NACA2410 aerofoil profile as initial aerofoil profile, and its concrete steps are:

Step 1 is determined target lift L according to designing requirement ₀The initial aerofoil profile of aerofoil adjusting mechanism is set to the NACA2410 aerofoil profile, obtains the displacement s of each row actuator ₁, s ₂..., s ₅₀Open wind-tunnel to the experiment of drying of the empirical model of initial aerofoil profile, aerodynamic balance is measured the 50 row actuator lift c at corresponding application point place separately _0l1, c _0l2..., c _0l50, and give center-controlling computer with this lift data information transfer, calculate the lift under the initial aerofoil profile

And storage L, the displacement s of initial each the row actuator of record ₁, s ₂..., s ₅₀The corresponding position of action point of described 50 row actuator and number are all consistent with position and the number of wing blasting Model Design point.

Step 2 provides population S1 at random, and the individuality that this population S1 comprises is the displacement variable Δ s of 50 row actuator of aerofoil adjusting mechanism ₁, Δ s ₂..., Δ s ₃₄, put genetic iteration time counter t=1 simultaneously.

Step 3, center-controlling computer is transferred to the displacement variable data message that obtains each row actuator of aerofoil adjusting mechanism by actuator controller, each row actuator is made corresponding displacement adjustment after receiving change in displacement information, change airfoil shape thereby promote support movements.

After step 4, new airfoil shape are adjusted out by adjusting mechanism, open wind-tunnel to the empirical model experiment of drying; Aerodynamic balance measure thereupon each row actuator of empirical model the lift c at corresponding application point place _L1, c _L2... c _L50, and give center-controlling computer with this lift data information transfer.

After step 5, center-controlling computer receive each lift data of optimizing point, calculate the lift summation at these some places And will

L compares with lift, if

Be not less than lift L, then

And the value of storage L and to store current displacement variable be that population S1 is in storage unit S; Compare L and target lift L ₀Size, if L is not less than L ₀, then program stops, and be met the aerofoil profile of target lift requirement, and current aerofoil profile is the aerofoil profile that satisfies the requirement of target lift; If L is less than L ₀, the size between the largest optimization iterations T=100 of count value t and setting in the counter relatively, if t less than T then proceed heredity and calculate, otherwise program termination.When largest optimization iterations T that count value t in the counter equals to set, be that count value t and largest optimization iterations T are at 100 o'clock in the counter, displacement variable is exactly to the required displacement variable of maximum lift aerofoil profile by initial aerofoil profile among the storage unit S.

Step 6 is passed through formula

$p\left(i\right)=\frac{c_{\mathrm{li}}}{\underset{j=1}{\overset{50}{\mathrm{\Σ}}}{c}_{\mathrm{lj}}},(1\≤i\≤50)$

Determine each individual Δ s among the population S1 _iCorresponding selection Probability p (i).And utilize formula according to the selection Probability p (i) that obtains

$q\left(i\right)=\underset{j=1}{\overset{i}{\mathrm{\Σ}}}p\left(i\right),(1\≤i\≤50)$

Calculate each individual Δ s _iCorresponding cumulative probability q (i).In [0,1] interval, produce 50 equally distributed random number r at random ₁, r ₂R ₅₀, if r _i≤ q (1) then chooses first the individual Δ s among the population S1 ₁As the new S ' of colony ₁If one of them individuality is q (k-1)≤r _i≤ q (k), (2≤k≤50,2≤i≤50) then choose k individual Δ s _kAs the new S ' of colony ₁One of them individuality utilizes this method with random number r ₁, r ₂R ₅₀One by one with cumulative probability q (i) thus relatively select 50 and individually form the new S ' of colony ₁

Step 7 is to the S ' of colony that newly obtains ₁In individual Δ s ' ₁, Δ s ' ₂..., Δ s ' ₅₀It is right that random pair produces 25 individualities, with back eight in the sixteen bit binary code of the displacement variable of intercoursing this individuality representative of expression between a pair of individuality, thereby form 50 new individualities, and new individually replace the former individual new population S2 that forms with what produce, namely 50 row actuator of aerofoil adjusting mechanism are with respect to the displacement variable Δ s of initial displacement " ₁, Δ s " ₂..., Δ s " ₅₀

Step 8 as population of new generation, namely replaces S1 with S2 with the S2 of colony, counter t=t+1, and repeating step 3 is to step 8, until the requirement of satisfying step 5.

Claims (6)

1. a device of adjusting wing blasting model wing surface is characterized in that, described wing blasting model wing surface adjusting gear comprises supporting mechanism (9) and control gear; Wherein

A. the supporting base (1) in the supporting mechanism (9) is tabular, the tangential equal in length of its width and wing blasting model, and its length is identical to length with the exhibition of wing blasting model; Actuator in the supporting mechanism (9) has many rows, be distributed on the supporting base (1) along supporting base (1) length direction, and first row's actuator is positioned at 16.7% place of supporting base (1) length, and last row's actuator is positioned at 83.3% place of supporting base (1) length; Every row's actuator is made up of a plurality of actuator; Each actuator lays respectively on each design point of this wing, and corresponding with the horizontal ordinate of each design point of this wing; Described actuator (5) is mounted in pairs in upper surface and the lower surface of supporting base (1); The a plurality of actuator that are in same row on the same surface link together by a data lines, are used for accepting same control signal and making the constant amplitude displacement;

B. control gear comprises center-controlling computer (7), piezoelectric type actuator controller (8) and aerodynamic balance (10); The aerodynamic balance (10) that is positioned at the wing model skin-surface is transferred to center-controlling computer (7) by data line with flow field data message D3; Center-controlling computer (7) transfers to piezoelectric type actuator controller (8) with the deflection of determining by steering order D1; Piezoelectric type actuator controller (8) is electric signal D2 with the instruction transformation that receives, and is transferred to each actuator (5) in the supporting mechanism (9); Each actuator (5) is according to the height of each the self-adjusting mobile terminal of deflection signal that receives, and then realize adjustment to wing model skin-surface height by the support bar of the bracing frame (3) that is connected with each actuator (5) mobile terminal, thereby realize the adjustment to aerofoil; Each actuator (5) is done the constant amplitude displacement along the wing model exhibition to each actuator of arranging when action.

2. a kind of device of adjusting wing blasting model wing surface according to claim 1 is characterized in that, the quantity of the actuator on the quantity of described bracing frame (3) and each row is identical; Bracing frame (3) is formed by supporting traverse with the orthogonal a plurality of support bars of supporting traverse; The exhibition appearance of the length of supporting traverse and wing together; The length of a plurality of support bars is identical, and the position of each support bar is corresponding with the position of the last every row actuator mounting hole of supporting base (1); One end of support bar is the external thread external thread rod in the same way with actuator (5) mobile terminal; The bar footpath of support bar is identical with the external diameter of actuator (5) mobile terminal.

3. a kind of device of adjusting wing blasting model wing surface according to claim 1, it is characterized in that, sleeve (4) in the supporting mechanism (9) is inner thread sleeve, by this sleeve (4) mobile terminal of actuator (5) and the support bar of bracing frame (3) is linked together.

4. a kind of device of adjusting wing blasting model wing surface according to claim 1, it is characterized in that, described wing model covering covers on the supporting traverse of bracing frame (3), realize adjustment to the wing cover surface configuration by the height of adjusting each support bar in the bracing frame (3), to obtain the wing model of different aerofoil profiles.

5. a kind of device of adjusting wing blasting model wing surface according to claim 1 is characterized in that, the position of every row's actuator mounting hole is corresponding with the horizontal ordinate of the design point of this place's upper surface of the airfoil; The quantity of every row's actuator mounting hole is counted identical with the design point of this place's upper surface of the airfoil.

6. wing blasting model wing surface method of adjustment is characterized in that its concrete steps are:

Step 1 is determined target lift L according to designing requirement ₀The initial aerofoil profile of aerofoil adjusting mechanism is set, obtains the initial displacement amount s of each row actuator ₁, s ₂..., s _a, wherein a is the quantity of Airfoil Design point; To the experiment of drying of the empirical model of initial aerofoil profile, obtain each row actuator the lift c at corresponding application point place _0l1, c _0l2..., c _0lbWith each row actuator the lift c at corresponding application point place _0l1, c _0l2..., c _0lbBe transferred to center-controlling computer, obtain the lift of initial aerofoil profile

Each row actuator the corresponding application point b that counts identical with the quantity of Airfoil Design point; The lift L of storing initial aerofoil profile and actuator initial displacement amount s ₁, s ₂..., s _a

Step 2 provides population S1 at random, and the individuality that this population S1 comprises is the displacement variable Δ s of each row actuator of aerofoil adjusting mechanism ₁, Δ s ₂..., Δ s _c, wherein c is identical with the quantity of Airfoil Design point; Put genetic iteration time counter t=1 simultaneously; The displacement variable of population S1 is transferred to center-controlling computer;

Step 3, center-controlling computer is respectively organized actuator with the displacement variable data message that obtains by what actuator controller was transferred to the aerofoil adjusting mechanism, each is organized actuator and makes corresponding displacement adjustment according to after the change in displacement information that receives, and obtains new airfoil shape;

Step 4 is to the experiment of drying of wing blasting model; Aerodynamic balance measure empirical model respectively organize actuator the lift c at corresponding application point place _L1, c _L2..., c _LmWherein m is identical with the quantity of Airfoil Design point; Give center-controlling computer with this lift data information transfer;

Step 5, by center-controlling computer calculate respectively organize actuator the lift summation at corresponding application point place

And will

Compare with the lift L of aerofoil profile, if

Be not less than lift L, obtain current lift

Storing the value of L and storing current displacement variable is that population S1 is in storage unit S; Compare L and target lift L ₀Size, if L is not less than L ₀, then program stops, and be met the aerofoil profile of target lift requirement, and current aerofoil profile is the aerofoil profile that satisfies the requirement of target lift; If L is less than target lift L ₀, the size between the largest optimization iterations T=100 of count value t and setting in the counter relatively is if t is less than T then proceed heredity and calculate, the program termination if t equals T; When largest optimization iterations T that count value t in the counter equals to set, displacement variable is exactly to the required displacement variable of maximum lift aerofoil profile by initial aerofoil profile among the storage unit S;

Step 6 is passed through formula

$p\left(i\right)=\frac{c_{l_i}}{\underset{j=1}{\overset{m}{\mathrm{\Σ}}}{c}_{l_j}},(1\≤i\≤m)$

Determine each individual Δ s among the population S1 _iCorresponding selection Probability p (i); And utilize formula according to the selection Probability p (i) that obtains

$q\left(i\right)=\underset{j=1}{\overset{i}{\mathrm{\Σ}}}p\left(i\right),(1\≤i\≤m)$

Determine each individual Δ s _iCorresponding cumulative probability q (i); In [0,1] interval, produce equally distributed random number r at random ₁, r ₂..., r _n, wherein n is identical with the quantity of Airfoil Design point; If r _i≤ q (1) then chooses first the individual Δ s among the population S1 _iAs the new S ' of colony ₁If one of them individuality is q (k-1)≤r _i≤ q (k), (2≤k≤m, 2≤i≤n) then choose k individual Δ s _kAs the new S ' of colony ₁One of them individuality; With random number r ₁, r ₂..., r _nRelatively form the new S ' of colony with cumulative probability q (i) one by one ₁The described quantity that produces equally distributed random number in [0,1] interval at random is consistent with the quantity of wing blasting Model Design point; The described S ' of colony ₁All the quantity with wing blasting model is identical for middle individual quantity;

Step 7 is to the S ' of colony that obtains ₁In individuality carry out random pair; With back eight in the sixteen bit binary code of the displacement variable of intercoursing this individuality representative of expression between a pair of individuality, thereby form new individuality, and new individually replace former individual new population S2, i.e. the displacement variable Δ s of the actuator of aerofoil adjusting mechanism of forming with what produce " ₁, Δ s " ₂..., Δ s " _p, wherein p is identical with the quantity of Airfoil Design point;

Step 8 as population of new generation, namely replaces S1 with S2 with the S2 of colony, counter t=t+1, and repeating step 3 is to step 8, until the requirement of satisfying step 5.

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