CN106777495A - The method that rotor-blade airfoil pitching moment is controlled by localized parameterization repairing type - Google Patents
The method that rotor-blade airfoil pitching moment is controlled by localized parameterization repairing type Download PDFInfo
- Publication number
- CN106777495A CN106777495A CN201611031930.9A CN201611031930A CN106777495A CN 106777495 A CN106777495 A CN 106777495A CN 201611031930 A CN201611031930 A CN 201611031930A CN 106777495 A CN106777495 A CN 106777495A
- Authority
- CN
- China
- Prior art keywords
- coordinate
- trailing edge
- interval
- rotor
- aerofoil profile
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Wind Motors (AREA)
Abstract
The present invention is directed to during rotor-blade airfoil is designed it is possible that pitching moment situation bigger than normal, by the geometric shape Torque-adjusting for changing aerofoil profile, pressure change based on aerofoil profile rear portion is to the maximum principle of pitching moment contribution, the method that proposition is modified to rotor-blade airfoil trailing edge.The stalling characteristic of aerofoil profile High Angle of Attack, therefore it is further proposed that modification aerofoil profile lower surface trailing edge, such as the following table facial contour in the interval of X-coordinate 0.9~1.0 may be influenceed due to trailing edge upper surface repairing type.Due to usual craft repairing type, to be easily caused profile rough, the method for employing airfoil trailing edge lower surface that Hicks Henne type functions are added to, ensure that smooth-shaped, torque is improved has positive effect, it is simultaneously little on the influence of other aerodynamic characteristics, satisfied torque factor is obtained by adjustment several times, effectiveness of the invention is demonstrated by calculating.
Description
Technical field
It is specially a kind of to control rotor-blade airfoil to bow by localized parameterization repairing type the present invention relates to rotor-blade airfoil design field
The method for facing upward torque.
Background technology
Rotor-blade airfoil is Rotor Aerodynamics Shape basic element, has important to lifting airscrew flow field and aerodynamic characteristic
Influence, be one of key technology that helicopter is developed.The pitching moment of rotor-blade airfoil directly affects the pitching moment of rotor,
And then determine weight, the size of feather mechanical device and power set.Excessive pitching moment will cause bending moment
Device is overweight, and power demand is too big, when influenceing the voyage of helicopter with boat.Therefore torque factor is the key characteristic of rotor-blade airfoil
One of.
The rotor-blade airfoil of current design both at home and abroad generally all has that pitching moment is excessive, on the one hand main cause is
Be design when torque constrain to it is inadequate, when causing comprehensive assessment torque factor under certain conditions torque factor be unsatisfactory for will
Ask, be on the other hand that numerical computations have certain error, possible numerical computations with wind tunnel test in terms of torque factor prediction
Meet design requirement, but results of wind tunnel shows to be unsatisfactory for design requirement.Therefore exist carries out repairing type to adjust to aerofoil profile
The demand of whole pitching moment.
If aerofoil profile is unsatisfactory for torque constraints, common processing method is to re-start optimization, strengthens torque constraint,
Or by manual repairing type.The problem that re-optimization design is present be workload it is big, it is necessary to substantial amounts of computing resource and manpower into
This, and optimum results differ and surely meet design requirement, such as maximum lift coefficient may decline, and drag divergence Mach number is attached
Near Resistance Value may increase.The problem that manual repairing type is present is possible to cause aerofoil profiles rough, causes pressure point
Cloth is rough, while manual repairing type efficiency is low, workload is big.
The content of the invention
To solve the problems, such as prior art, the present invention proposes a kind of by the localized parameterization repairing type control rotor wing
The method of type pitching moment, localized parameterization is carried out to airfoil trailing edge lower surface, and the local form for parameterizing is entered using parameter
The quick repairing type of row, obtains new smooth geometric shape, then carry out Aerodynamic characteristics and the precise control wing based on new profile
Type pitching moment is a kind of quick repairing type to meet the side that aerofoil profile pitching moment design requirement and other characteristics are held essentially constant
Method.
The technical scheme is that：
A kind of method that rotor-blade airfoil pitching moment is controlled by localized parameterization repairing type, it is characterised in that：Including
Following steps：
Step 1：The base profile of repairing type is treated in selection, and the base profile meets maximum lift coefficient, lift-drag ratio design will
Ask；
Step 2：Line parameter, wherein a values model are entered to the curve in base profile trailing edge lower surface X-coordinate interval (a, b)
Enclose is (0.88,0.92), b spans (0.98,1.0)：
Step 2.1：It is (0,1) area that the X-coordinate of the base profile following table surface curve in interval (a, b) is passed through into linear transformation
Between, Y-coordinate keeps constant；
Step 2.2：Selection design variable, using Hicks-Henne type functions, in (0,1) area that step 2.1 conversion is obtained
One Y-coordinate disturbance curve of interior generation；
Step 2.3：After the Y-coordinate disturbance curve that step 2.2 is obtained switches back to (a, b) interval, be added to base profile
In trailing edge lower surface (a, b) is interval in the Y-coordinate of point, new aerofoil profile is obtained；
Step 3：New aerofoil profile to obtaining carries out aerodynamic characteristic assessment, and whether inspection torque factor meets requirement, if
It is unsatisfactory for, the design variable to choosing is adjusted, and is then back to step 2.2, is required until torque factor meets.
Further preferred scheme, a kind of side by localized parameterization repairing type control rotor-blade airfoil pitching moment
Method, it is characterised in that：Y-coordinate is disturbed into curve combining to base profile trailing edge lower surface in step 2, under the new aerofoil profile for obtaining
Surface Y-coordinate expression formula is：
Wherein yl0X airfoil trailing edge following table surface function on the basis of (), N is design variable number, ckIt is design variable, fk(x)
It is Hicks-Henne type functions：
fk(x)=sin4(πxe(k))
WhereinxkIt is the parametric variable of Hicks-Henne type functions.
Further preferred scheme, a kind of side by localized parameterization repairing type control rotor-blade airfoil pitching moment
Method, it is characterised in that：Aerodynamic characteristic assessment is carried out in step 3 to the new aerofoil profile for obtaining, assessment requires that torque factor meets and sets
Meter required, and maximum lift coefficient and lift-drag ratio can not be corresponded to less than base profile maximum lift coefficient and lift-drag ratio
99.2%.
Beneficial effect
The present invention carries out localized parameterization by airfoil trailing edge lower surface, and the local form for parameterizing is entered using parameter
The quick repairing type of row, obtains new smooth geometric shape, then carry out Aerodynamic characteristics and the precise control wing based on new profile
Type pitching moment.Present invention employs the method for airfoil trailing edge lower surface that Hicks-Henne type functions are added to, ensure that
Smooth-shaped, pitching moment is improved has positive effect, while little on the influence of other aerodynamic characteristics.Embodiment is by calculating
Demonstrate effectiveness of the invention.
Additional aspect of the invention and advantage will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by practice of the invention.
Brief description of the drawings
Of the invention above-mentioned and/or additional aspect and advantage will become from description of the accompanying drawings below to embodiment is combined
Substantially and be readily appreciated that, wherein：
Geometric shape compares figure before and after the modification of Fig. 1 aerofoil profiles；
Geometric shape compares partial enlarged drawing before and after the modification of Fig. 2 aerofoil profiles；
Pressure distribution compares figure before and after the modification of Fig. 3 aerofoil profiles；
Fig. 4 low speed maximum lift coefficients compare；
Fig. 5 low speed pitching moment coefficients compare；
Fig. 6 low speed lift-drag ratios compare；
Fig. 7 zero lift moment coefficients comparisons；
Fig. 8 zero-lift drag coefficients compare.
Specific embodiment
Embodiments of the invention are described below in detail, the embodiment is exemplary, it is intended to for explaining the present invention, and
It is not considered as limiting the invention.
The purpose of the present invention is to realize the quick repairing type to rotor-blade airfoil, the design requirement for making it meet pitching moment, together
When big influence is not produced to other aerodynamic characteristics.Therefore, the present invention proposes a kind of localized parameterization repairing type that passes through controls rotation
The method of thriving type pitching moment, localized parameterization is carried out to airfoil trailing edge lower surface, using parameter to the local outer of parametrization
Shape carries out quick repairing type, obtains new smooth geometric shape, then carry out Aerodynamic characteristics based on new profile and accurately control
Aerofoil profile pitching moment processed, is that a kind of quick repairing type is held essentially constant with meeting aerofoil profile pitching moment design requirement and other characteristics
Method.
Specifically include following steps：
Step 1：The base profile of repairing type is treated in selection, and the base profile meets maximum lift coefficient, lift-drag ratio design will
Ask；
Step 2：Line parameter, wherein a values model are entered to the curve in base profile trailing edge lower surface X-coordinate interval (a, b)
Enclose is (0.88,0.92), b spans (0.98,1.0)：
Step 2.1：It is (0,1) area that the X-coordinate of the base profile following table surface curve in interval (a, b) is passed through into linear transformation
Between, Y-coordinate keeps constant；
Step 2.2：Selection design variable, using Hicks-Henne type functions, in (0,1) area that step 2.1 conversion is obtained
One Y-coordinate disturbance curve of interior generation；
Step 2.3：After the Y-coordinate disturbance curve that step 2.2 is obtained switches back to (a, b) interval, be added to base profile
In trailing edge lower surface (a, b) is interval in the Y-coordinate of point, new aerofoil profile is obtained；
Step 3：New aerofoil profile to obtaining carries out aerodynamic characteristic assessment, and whether inspection torque factor meets requirement, if
It is unsatisfactory for, the design variable to choosing is adjusted, and is then back to step 2.2, is required until torque factor meets.
Further, Y-coordinate is disturbed into curve combining to base profile trailing edge lower surface, the new wing for obtaining in step 2
Type lower surface Y-coordinate expression formula is：
Wherein yl0X airfoil trailing edge following table surface function on the basis of (), N is design variable number, ckIt is design variable, fk(x)
It is Hicks-Henne type functions：
fk(x)=sin4(πxe(k))
WhereinxkIt is the parametric variable of Hicks-Henne type functions.
Further, aerodynamic characteristic assessment is carried out to the new aerofoil profile for obtaining in step 3, assessment requires that torque factor is expired
Sufficient design requirement, and maximum lift coefficient and lift-drag ratio can not be corresponded to less than base profile maximum lift coefficient and lift-drag ratio
99.2%.
Illustrated based on above-mentioned steps, specific embodiment is given below：
The base profile of the present embodiment is obtained by optimization, and its maximum lift coefficient, lift-drag ratio meet design requirement, profile
As shown in Original foil in Fig. 1.
Line parameter is entered to the curve in base profile trailing edge lower surface X-coordinate interval (0.9,1.0)：
First, it is (0,1) X-coordinate of the base profile following table surface curve in interval (0.9,1.0) to be passed through into linear transformation
Interval, Y-coordinate keeps constant；
Secondly, design variable is selected, using Hicks-Henne type functions, (0,1) obtained in step 2.1 conversion is interval
One Y-coordinate disturbance curve of interior generation；
Finally, after the Y-coordinate disturbance curve for step 2.2 being obtained switches back to (a, b) interval, be added to base profile trailing edge
In lower surface (a, b) is interval in the Y-coordinate of point, new aerofoil profile is obtained.
The new aerofoil profile lower surface Y-coordinate expression formula for obtaining is：
Wherein yl0Airfoil trailing edge following table surface function, N=2, c on the basis of (x)kIt is design variable, initial value takes c1=
0.0005, c2=0.0002, fkX () is Hicks-Henne type functions：
fk(x)=sin4(πxe(k))
Whereinx1=0.6, x2=0.75.
New aerofoil profile to obtaining carries out aerodynamic characteristic assessment, and whether inspection torque factor meets requirement, and requires it
Aerodynamic characteristic in terms of him is not reduced substantially, and judgment criteria is that maximum lift coefficient and lift-drag ratio can not be corresponded in the present embodiment
Less than the 99.2% of base profile maximum lift coefficient and lift-drag ratio.If being unsatisfactory for above-mentioned standard, to the design variable chosen
ckIt is adjusted, is then back to iterative calculation, is required until torque factor meets.
The new aerofoil profile that the satisfaction that the present embodiment is obtained is required is as shown in New foil in Fig. 1, and enlarged drawing is as shown in Figure 2.
Calculating state in the present embodiment is Ma=0.5, Alpha=3.0 °, Re=2.4E6, the pressure distribution before and after modification with it is pneumatic
Property comparison is as shown in Figure 3 and Table 1.
Aerodynamic characteristic compares before and after the modification of the aerofoil profile of table 1
| Aerofoil profile | Lift coefficient | Moment coefficient |
| Initial aerofoil profile | 0.49846 | -0.75153E-02 |
| After modification | 0.49480 | -0.65791E-02 |
New aerofoil profile low speed maximum lift coefficient is with drag divergence Property comparison as Figure 4-8, it is seen that right before and after modification
Aerofoil profile torque improvement result is obvious, but otherwise aerodynamic characteristic is not reduced substantially.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from principle of the invention and objective
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (3)
1. it is a kind of by localized parameterization repairing type control rotor-blade airfoil pitching moment method, it is characterised in that：Including following step
Suddenly：
Step 1：The base profile of repairing type is treated in selection, and the base profile meets maximum lift coefficient, lift-drag ratio design requirement；
Step 2：Line parameter is entered to the curve in base profile trailing edge lower surface X-coordinate interval (a, b), wherein a spans are
(0.88,0.92), b spans (0.98,1.0)：
Step 2.1：By the X-coordinate of the base profile following table surface curve in interval (a, b) by linear transformation for (0,1) is interval, Y
Coordinate keeps constant；
Step 2.2：Selection design variable, using Hicks-Henne type functions, (0,1) obtained in step 2.1 conversion is interval interior
One Y-coordinate disturbance curve of generation；
Step 2.3：After the Y-coordinate disturbance curve that step 2.2 is obtained switches back to (a, b) interval, be added to base profile trailing edge
In lower surface (a, b) is interval in the Y-coordinate of point, new aerofoil profile is obtained；
Step 3：New aerofoil profile to obtaining carries out aerodynamic characteristic assessment, and whether inspection torque factor meets requirement, if discontented
Foot, the design variable to choosing is adjusted, and is then back to step 2.2, is required until torque factor meets.
2. a kind of method that rotor-blade airfoil pitching moment is controlled by localized parameterization repairing type according to claim 1, it is special
Levy and be：Y-coordinate is disturbed into curve combining to base profile trailing edge lower surface in step 2, the new aerofoil profile lower surface Y for obtaining sits
Marking expression formula is：
Wherein yl0X airfoil trailing edge following table surface function on the basis of (), N is design variable number, ckIt is design variable, fkX () is
Hicks-Henne type functions：
fk(x)=sin4(πxe(k))
WhereinxkIt is the parametric variable of Hicks-Henne type functions.
3. a kind of method that rotor-blade airfoil pitching moment is controlled by localized parameterization repairing type according to claim 1, it is special
Levy and be：Aerodynamic characteristic assessment is carried out in step 3 to the new aerofoil profile for obtaining, assessment requires that torque factor meets design requirement,
And maximum lift coefficient and lift-drag ratio can not be corresponded to and be less than the 99.2% of base profile maximum lift coefficient and lift-drag ratio.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611031930.9A CN106777495B (en) | 2016-11-22 | 2016-11-22 | Method for controlling rotor wing profile pitching moment through local parametric modification |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611031930.9A CN106777495B (en) | 2016-11-22 | 2016-11-22 | Method for controlling rotor wing profile pitching moment through local parametric modification |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106777495A true CN106777495A (en) | 2017-05-31 |
| CN106777495B CN106777495B (en) | 2020-01-17 |
Family
ID=58970939
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611031930.9A Active CN106777495B (en) | 2016-11-22 | 2016-11-22 | Method for controlling rotor wing profile pitching moment through local parametric modification |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106777495B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229417A (en) * | 2018-08-06 | 2019-01-18 | 浙江工业大学 | A kind of bionical combined-wing type design method based on the carving wing |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104978449A (en) * | 2015-08-17 | 2015-10-14 | 北京航空航天大学 | Aerodynamic optimization method of leading edge slats position and trailing edge flap position of two-dimensional three-section airfoil profile |
| CN105905296A (en) * | 2016-05-18 | 2016-08-31 | 北京理工大学 | Single-wing gyrating aircraft lift force optimized design method based on spinning stability |
-
2016
- 2016-11-22 CN CN201611031930.9A patent/CN106777495B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104978449A (en) * | 2015-08-17 | 2015-10-14 | 北京航空航天大学 | Aerodynamic optimization method of leading edge slats position and trailing edge flap position of two-dimensional three-section airfoil profile |
| CN105905296A (en) * | 2016-05-18 | 2016-08-31 | 北京理工大学 | Single-wing gyrating aircraft lift force optimized design method based on spinning stability |
Non-Patent Citations (2)
| Title |
|---|
| 王元元 等: "Robust airfoil optimization based on improved particle swarm optimization method", 《APPLIED MATHEMATICS AND MECHANICS》 * |
| 王建军 等: "HicksHenne翼型参数化方法分析及改进", 《航空计算技术》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229417A (en) * | 2018-08-06 | 2019-01-18 | 浙江工业大学 | A kind of bionical combined-wing type design method based on the carving wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106777495B (en) | 2020-01-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106314791B (en) | The aerofoil profile of rotor blade for rotor blade aircraft | |
| CN105752314B (en) | A kind of high-altitude low speed Natural Laminar Flow high-lift airfoil | |
| JP7401545B2 (en) | Rotor blades and their design methods | |
| Maughmer | Design of winglets for high-performance sailplanes | |
| US8066219B2 (en) | Anhedral tip blades for tiltrotor aircraft | |
| CN1280538C (en) | Air foil configuration for wind turbine | |
| CN1084696C (en) | Blade profile for aircraft rotor and rotor comprising same | |
| CN107145677B (en) | Improved geometric parameter airfoil design method | |
| CN102941925B (en) | Elastic correction method of airplane lifting resistance aerodynamic characteristics | |
| CN103277245A (en) | Large-thickness blunt-trailing-edge wind-power airfoil profiles and a design method thereof | |
| CN106741925A (en) | The thickness rotor-blade airfoil of high-lift Low-torque characteristic 12% under the conditions of a kind of full working scope | |
| CN111017248B (en) | Static aeroelasticity correction method for airplane wing | |
| CN106777495A (en) | The method that rotor-blade airfoil pitching moment is controlled by localized parameterization repairing type | |
| CN104863799A (en) | Method for designing wind turbine airfoil by using Bessel function curve | |
| CN106741923A (en) | The thickness rotor-blade airfoil of high-lift Low-torque characteristic 7% under the conditions of a kind of full working scope | |
| US20210009256A1 (en) | Elliptical wing tip and method of fabricating same | |
| CN106828876A (en) | A kind of sweepforward natural laminar flow wing suitable for medium or short range high speed civil aircraft | |
| CN106741924A (en) | A kind of high lift-drag ratio Low-torque characteristic 9% thickness rotor-blade airfoil under the conditions of full working scope | |
| CN204507266U (en) | Low induced drag lifting airscrew anti-under a kind of wing tip sweepback | |
| CN101886619B (en) | Special airfoil for blade tip of wind driven generator | |
| CN110110444A (en) | One kind is towards large-scale merchant ship coupled mode wing sail optimization method and system | |
| CN107487438A (en) | A kind of high-lift airfoil | |
| CN106777590A (en) | A kind of air-foil matches method for designing | |
| CN205418070U (en) | Class triangle overall arrangement high altitude screw | |
| CN114154270A (en) | Design method for power-increasing trailing edge flap of blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |