CN106114821B - A kind of design method and propeller configurations of aircraft with low noise propeller - Google Patents
A kind of design method and propeller configurations of aircraft with low noise propeller Download PDFInfo
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- CN106114821B CN106114821B CN201610451785.3A CN201610451785A CN106114821B CN 106114821 B CN106114821 B CN 106114821B CN 201610451785 A CN201610451785 A CN 201610451785A CN 106114821 B CN106114821 B CN 106114821B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
Abstract
The present invention provides a kind of design method of aircraft with low noise propeller, including：S100：According to the substantially leaf progress CFD computational fluid dynamics calculating of preset aircraft propeller, leaf corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angles of attack is obtained；S200：Blade momentum theory calculating is carried out according to preset environmental gas flow regime and propeller geometric parameter and lift coefficient and resistance coefficient, obtains the air force data of propeller；S300：FW H aeroacoustics equation calculations, which are carried out, according to the air force data of preset propeller geometric parameter and propeller obtains the noise characteristic data of propeller；S400：The optimization algorithm cycle based on simulated annealing thought is called to execute step S200 to S300, until noise characteristic Data Convergence, obtains the optimal geometrical parameter of propeller.The present invention takes into account the power and noise problem of propeller simultaneously, greatly reduces the noise that aircraft generates in flight course.
Description
This case be with application No. is 201510280181.2, it is entitled《A kind of design side of aircraft with low noise propeller
Method》Patent application be female case divisional application.
Technical field
The present invention relates to aircraft fields, particularly relate to a kind of design method of aircraft with low noise propeller.
Background technology
The Design of Propeller of the small-sized quadrotor of the prior art is based primarily upon from the aspect of two：First, design
Propeller lifting resistance characteristic to meet the requirement of quadrotor load-carrying, mobility and power of motor；Second, ensure pneumatic
The work noise of propeller is reduced under the premise of characteristic as far as possible.
Existing Design of Propeller mostly uses greatly the design method of peak efficiency on domestic and international market at present, and to noise water
It is flat to consider deficiency, and mostly conventional aircraft provides pulling force or thrust, is set almost without specifically for small-sized quadrotor
The low noise propeller of meter.Quadrotor is to have obviously in terms of operating condition with propeller used in conventional aircraft
Difference, therefore, also need to further study promotion for the Design Method of Propeller of quadrotor.
It is entitled if number of patent application is 201410398306.7《Hypersonic aircraft CFD aerodynamic modeling methods》's
Patent of invention is finally obtained to successively passing through CFD pre-treatments, CFD solvers and CFD post-processing three phases after Modeling of Vehicle
The aerodynamic characteristic of aircraft provides reliable foundation for the design of aircraft, and saves development cost.But without special needle
A kind of design method that can reduce noise is provided to the propeller of aircraft, and is directed to the prior art to obtain propeller gas
Dynamic and noise characteristic and Fluid Mechanics Computation (Computational Fluid Dynamics, the CFD) method generally used, though
It so says and can be good at solving fluid mechanics problem in conjunction with computer hardware computing capability and mathematics numerical computation method, and with
The fast development of Fluid Mechanics Computation (CFD approach), solving result is also more accurate.But its time overhead is to allow
What people was difficult to receive, continue to optimize development especially with propeller, it is desirable to be able to quickly obtain propeller startup and
Noise characteristic show that pneumatic and noise characteristic starts to cannot be satisfied the demand of people, therefore, it is necessary to provide using CFD approach
A kind of solution period that can shorten flight vehicle aerodynamic and noise characteristic, and vehicle spin can be reduced according to solving result
The method of paddle noise.
Invention content
The technical problem to be solved by the present invention is to：A kind of design method of aircraft with low noise propeller is provided, it can
Obtain having both the aircraft propeller of aerodynamic characteristic and low noise feature.
In order to solve the above-mentioned technical problem, the technical solution adopted by the present invention is：
A kind of design method of aircraft with low noise propeller, including：
S100：According to the substantially leaf progress CFD computational fluid dynamics calculating of aircraft propeller, obtain described leaf
Corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angles of attack；
S200：According to preset environmental gas flow regime, preset propeller geometric parameter and the lift coefficient
Blade momentum theory calculating is carried out with resistance coefficient, obtains the air force data of the propeller；
S300：The pneumatic sound of FW-H is carried out according to the air force data of preset propeller geometric parameter and the propeller
It learns equation calculation and obtains the noise characteristic data of propeller；
S400：The optimization algorithm cycle based on simulated annealing thought is called to execute step S200 to S300, until described make an uproar
Sound characteristics Data Convergence obtains the geometric parameter of propeller.
The beneficial effects of the present invention are：The aircraft being different from the prior art pursues efficient flying quality simply,
And ignore the operating noise pollution that in flight course propeller generates, and then aircraft is caused to be wanted indoors etc. with low noise
The special occasions asked has the problem of using limiting, influencing user's flight experience.The present invention provides a kind of aircraft with low noise spiral shell
The design method for revolving paddle is first depending on just fixed leaf the progresss CFD calculating of propeller, obtain just fixed leaf middle different Reynolds number with
Lift coefficient in the case of the different angles of attack and resistance coefficient；Again according under specific environment residing for aircraft flowing gas state and
Just fixed leaf geometric parameter carries out the aerodynamic characteristic that propeller is calculated in blade momentum theory；Come again, according to expression spiral
The FW-H equation solutions of paddle noise signal characteristic obtain the noise characteristic of propeller；Finally, call optimization method to propeller
Aerodynamic characteristic, noise characteristic and the best geometric parameters that propeller is just obtained during fixed continuous cycle calculations of geometric parameter
Number.By the propeller configurations that the design method of aircraft with low noise propeller of the present invention obtains, not only ensure that winged
The aerodynamic characteristics such as load-carrying, the mobility and power requirement in flight course of row device；And noise characteristic has been taken into account simultaneously, Neng Gouyou
Effect reduces the aircraft noise pollution that propeller rotation generates in flight course；Further, optimize the flight of aircraft
Can, the flight experience of manipulator is improved, various occasions are suitable for.
Description of the drawings
Fig. 1 is a kind of flow diagram of the design method of aircraft with low noise propeller of the present invention；
Fig. 2 is a kind of flow diagram of the design method of aircraft with low noise propeller of the present invention；
Fig. 3 is a kind of flow diagram of the design method of aircraft with low noise propeller of the present invention.
Specific implementation mode
To explain the technical content, the achieved purpose and the effect of the present invention in detail, below in conjunction with embodiment and coordinate attached
Figure is explained.
The design of most critical of the present invention is：According to the substantially leaf progress CFD calculating of preset propeller and blade momentum
Theoretical calculation obtains the aerodynamic characteristic of propeller, then the propeller acoustic characteristic being calculated by FW-H, finally combines simulation
Annealing optimisation algorithm obtains the optimal geometrical parameter of propeller.
Explanation of nouns：
CFD：Computational fluid dynamics；Using electronic computer as tool, using the mathematical method of various discretizations, to fluid
All kinds of problems of mechanics carry out numerical experiment, computer mould fits analysis and research, to solve various practical problems；
FW-H equations：Aeroacoustics equation；
Reynolds number：A kind of dimensionless number that can be used to characterize fluid mobility status, the stream of fluid can be distinguished using Reynolds number
Dynamic is laminar flow or turbulent flow, it is also possible to determine that object flows suffered resistance in a fluid；
The angle of attack：For fixed wing aircraft, the direction of advance (direction for being equivalent to air-flow) and wing chord of wing are (with fuselage axis
It is different) angle the angle of attack, the also referred to as angle of attack, it is to determine the benchmark of wing posture in the gas flow, lift coefficient and resistance system
Number is all the function of the angle of attack, and in a certain range, the angle of attack is bigger, and lift coefficient is also bigger with resistance coefficient；
Lift coefficient：One characteristic, refer to lift suffered by object and the product of air-flow dynamic pressure and area of reference it
Than；
Resistance coefficient：For aircraft, resistance coefficient be defined as resistance suffered by object (such as aircraft, guided missile) with
The ratio between air-flow dynamic pressure and area of reference are a characteristics；
Propeller geometric parameter：Diameter D, blade number B including propeller, solidity σ, blade angle β, geometrical pitch H, reality
The propeller configurations parameter of border screw pitch Hg and theoreticalpiston HT；
Foline：Blade is made of the unlimited number of blade micro- section (i.e. foline) continuously arranged；
Convergence：A kind of offline mode of aircraft expands the first half of big gun jet pipe from large to small to middle shrinkage to one
Narrow larynx.Change from small to big again after narrow larynx and expands outwardly.Combustion gas by high pressure flow nozzle first half, pass through narrow larynx after by latter half of
Effusion
Air force data：The data collected based on aerodynamics；
Noise characteristic data：The data that noise characteristic based on aircraft in flight course collects；
Wing aerodynamic coefficient：Based on the coefficient of wing aerodynamic features, the air force of three-dimensional wing is referred to
Coefficient is to determine that flight air force is special with wing geometric shape, the changing rule of head on free stream Mach number, the angle of attack and yaw angle
The most important factor of property；
Velocity coeffficient initial value：The ratio between the speed of flying speed and air velocity of the aircraft in flight course it is initial
Value；
Velocity coeffficient：The ratio between the speed of flying speed and air velocity of the aircraft in flight course；
Time-derivative：How the instantaneous rate of change of functional value is determined when expression Functions in Time Domain independent variable variation；
Load noise：Aircraft run in the air and on the ground and transportational process in, the statistics for the noise that structure is born
It indicates.
Fig. 1 and Fig. 2 is please referred to, the present invention provides a kind of design method of aircraft with low noise propeller, including：
S100：According to the substantially leaf progress CFD computational fluid dynamics calculating of preset aircraft propeller, institute is obtained
State leaf corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angles of attack；
S200：According to preset environmental gas flow regime, preset propeller geometric parameter and the lift coefficient
Blade momentum theory calculating is carried out with resistance coefficient, obtains the air force data of the propeller；
S300：The pneumatic sound of FW-H is carried out according to the air force data of preset propeller geometric parameter and the propeller
It learns equation calculation and obtains the noise characteristic data of propeller；
S400：The optimization algorithm cycle based on simulated annealing thought is called to execute step S200 to S300, until described make an uproar
Sound characteristics Data Convergence obtains the geometric parameter of propeller.
As can be seen from the above description, the beneficial effects of the present invention are：The present invention provides a kind of aircraft with low noise propeller
Design method, be first depending on just fixed leaf the progresss CFD calculating of propeller, obtain just leaf middle different Reynolds number and difference calmly
Lift coefficient in the case of the angle of attack and resistance coefficient；Determine again with first according to the flowing gas state under specific environment residing for aircraft
Leaf geometric parameter carries out the aerodynamic characteristic that propeller is calculated in blade momentum theory；Come again, makes an uproar according to expression propeller
The FW-H equation solutions of acoustical signal characteristic obtain the noise characteristic of propeller；Finally, call optimization method in the gas to propeller
The optimal geometrical parameter of propeller is obtained during dynamic characteristic, noise characteristic and the just fixed continuous cycle calculations of geometric parameter.
By the propeller configurations that the design method of aircraft with low noise propeller of the present invention obtains, aircraft not only ensure that
The aerodynamic characteristics such as load-carrying, the mobility and power requirement in flight course；And noise characteristic has been taken into account simultaneously, it can effectively drop
The noise pollution that propeller rotation generates in flight course of low aircraft；Further, the flying quality for optimizing aircraft, carries
The flight experience of high manipulator is suitable for various occasions.
Further, step S200 is specifically included：
S201：According to the leaf different Reynolds number, the different angles of attack and preset propeller geometric parameter to propeller
Foline is divided, and foline group more than two is obtained；
S202：To corresponding to velocity coeffficient initial value and each foline group Reynolds number and the angle of attack calculate, obtain each leaf
Element organizes corresponding wing aerodynamic coefficient and velocity coeffficient；
S203：It is recycled using optimization algorithm and executes step S202 until convergence, obtains propeller air force data.
Further, step S300 is specifically included：
S301：Geometry number according to foline aerodynamic parameter, the propeller in the air force data of propeller
Propeller radius, rotating speed and observer's position coordinates in are iterated calculating, obtain delay time and opposite position vector；
S302：FW-H aeroacoustics equation calculations are carried out according to the delay time and opposite position vector, obtain F, M, opposite
The time-derivative and opposite position vector direction projection amount answered；
S303：The thickness and load of the single foline of the propeller are calculated using FW-H aeroacoustics Equation Approximates
Lotus noise；
S304：The thickness and load noise of single foline according to the propeller and the blade quantity of the propeller
The thickness and load noise of the propeller are obtained with foline quantity；
S305：The average sound pressure level of propeller is calculated according to the thickness and load noise of the propeller.
Further, further include by the leaf corresponding liter under different Reynolds number and the different angles of attack after step S100
Force coefficient and resistance coefficient embody in a tabular form.
Further, the aircraft is small-sized quadrotor.
Fig. 2 and Fig. 3 are please referred to, the embodiment of the present invention one is：
S100：According to the substantially leaf progress CFD computational fluid dynamics calculating of preset aircraft propeller, institute is obtained
State leaf corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angles of attack；
By the substantially leaf of pre-set flight device propeller, obtain and calculate basis；
S101：By leaf corresponding lift coefficient and the resistance coefficient under different Reynolds number and the different angles of attack with table
Case form embodies.
S200：According to preset environmental gas flow regime, preset propeller geometric parameter and the lift coefficient
Blade momentum theory calculating is carried out with resistance coefficient, obtains the air force data of the propeller；
The preset environmental gas flow regime refers to the environment residing for a default aircraft, such as indoor environment, room
External environment, outdoor strong wind atmosphere or the rainy day environment etc. of outdoor, each environment has corresponding specific environment gas
Flow regime；It is calculated by combining, obtains pneumatic spy of the propeller of aircraft under this specific environment gas circulation status
Property, provide operating basis for follow-up calculating.
It specifically includes：
S201：According to the leaf different Reynolds number, the different angles of attack and preset propeller geometric parameter to propeller
Foline is divided, and foline group more than two is obtained；
S202：To corresponding to velocity coeffficient initial value and each foline group Reynolds number and the angle of attack calculate, obtain each leaf
Element organizes corresponding wing aerodynamic coefficient and velocity coeffficient；
S203：It is recycled using optimization algorithm and executes step S202 until convergence, obtains propeller air force data.
S300：The pneumatic sound of FW-H is carried out according to the air force data of preset propeller geometric parameter and the propeller
It learns equation calculation and obtains the noise characteristic data of propeller；
It specifically includes：
S301：Geometry number according to foline aerodynamic parameter, the propeller in the air force data of propeller
Propeller radius R, rotating speed Q and observer's position coordinates in are iterated calculating, obtain delay time and opposite position vector；
S302：FW-H aeroacoustics equation calculations are carried out according to the delay time and opposite position vector, obtain F, M, opposite
The time-derivative and opposite position vector direction projection amount answered；
S303：The thickness and load of the single foline of the propeller are calculated using FW-H aeroacoustics Equation Approximates
Lotus noise；
S304：The thickness and load noise of single foline according to the propeller and the blade quantity of the propeller
The thickness and load noise of the propeller are obtained with foline quantity；
S305：The average sound pressure level of propeller is calculated according to the thickness and load noise of the propeller.
S400：The optimization algorithm cycle based on simulated annealing thought is called to execute step S200 to S300, until described make an uproar
Sound characteristics Data Convergence obtains the optimal geometrical parameter of propeller.In conclusion a kind of aircraft with low noise provided by the invention
The propeller configurations that the design method of propeller obtains not only ensure that aircraft load-carrying, mobility and work(in flight course
The requirement of the aerodynamic characteristics such as rate；And noise characteristic has been taken into account simultaneously, it can effectively reduce aircraft propeller in flight course
Rotate the noise pollution generated；Further, the flying quality for optimizing aircraft improves the flight experience of manipulator, is suitable for
Various occasions.
Example the above is only the implementation of the present invention is not intended to limit the scope of the invention, every to utilize this hair
Equivalents made by bright specification and accompanying drawing content are applied directly or indirectly in relevant technical field, include similarly
In the scope of patent protection of the present invention.
Claims (8)
1. a kind of design method of aircraft with low noise propeller, which is characterized in that including：
S100：According to the substantially leaf progress CFD computational fluid dynamics calculating of preset aircraft propeller, the leaf is obtained
Shape corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angles of attack；
S200：According to preset environmental gas flow regime, preset propeller geometric parameter and the lift coefficient and resistance
Force coefficient carries out blade momentum theory calculating, obtains the air force data of the propeller；
S300：The aeroacoustics sides FW-H are carried out according to the air force data of preset propeller geometric parameter and the propeller
The noise characteristic data of propeller are calculated in journey；
S400：The optimization algorithm cycle based on simulated annealing thought is called to execute step S200 to S300, until the noise is special
Property Data Convergence, obtains the geometric parameter of propeller；
Step S300 is specifically included：
S301：According to foline aerodynamic parameter, the preset propeller geometric parameters in the air force data of propeller
Propeller radius, rotating speed and observer's position coordinates in number are iterated calculating, obtain delay time and opposite position vector；
S302：FW-H aeroacoustics equation calculations are carried out according to the delay time and opposite position vector, obtain aerodynamic force F, Mach
Number M, corresponding time-derivative and opposite position vector direction projection amount；
S303：The thickness and load that the single foline of the propeller is calculated using FW-H aeroacoustics Equation Approximates are made an uproar
Sound；
S304：The thickness and load noise of single foline according to the propeller and the blade quantity and leaf of the propeller
Prime number measures the thickness and load noise of the propeller；
S305：The average sound pressure level of propeller is calculated according to the thickness and load noise of the propeller.
2. a kind of design method of aircraft with low noise propeller according to claim 1, which is characterized in that step S200
It specifically includes：
S201：According to the leaf different Reynolds number, the different angles of attack and preset propeller geometric parameter to propeller foline
It is divided, obtains foline group more than two；
S202：To corresponding to velocity coeffficient initial value and each foline group Reynolds number and the angle of attack calculate, obtain each foline group
Corresponding wing aerodynamic coefficient and velocity coeffficient；
S203：It is recycled using optimization algorithm and executes step S202 until convergence, obtains propeller air force data.
3. a kind of design method of aircraft with low noise propeller according to claim 1, which is characterized in that step S100
After further include by leaf corresponding lift coefficient and the resistance coefficient under different Reynolds number and the different angles of attack with table shape
Formula embodies.
4. a kind of design method of aircraft with low noise propeller according to claim 1, which is characterized in that the flight
Device is small-sized quadrotor.
5. a kind of propeller configurations, which is characterized in that the design method according to aircraft with low noise propeller is made：
S100：According to the substantially leaf progress CFD computational fluid dynamics calculating of preset aircraft propeller, the leaf is obtained
Shape corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angles of attack；
S200：According to preset environmental gas flow regime, preset propeller geometric parameter and the lift coefficient and resistance
Force coefficient carries out blade momentum theory calculating, obtains the air force data of the propeller；
S300：The aeroacoustics sides FW-H are carried out according to the air force data of preset propeller geometric parameter and the propeller
The noise characteristic data of propeller are calculated in journey；
S400：The optimization algorithm cycle based on simulated annealing thought is called to execute step S200 to S300, until the noise is special
Property Data Convergence, obtains the geometric parameter of propeller；
Step S300 is specifically included：
S301：According to foline aerodynamic parameter, the preset propeller geometric parameters in the air force data of propeller
Propeller radius, rotating speed and observer's position coordinates in number are iterated calculating, obtain delay time and opposite position vector；
S302：FW-H aeroacoustics equation calculations are carried out according to the delay time and opposite position vector, obtain aerodynamic force F, Mach
Number M, corresponding time-derivative and opposite position vector direction projection amount；
S303：The thickness and load that the single foline of the propeller is calculated using FW-H aeroacoustics Equation Approximates are made an uproar
Sound；
S304：The thickness and load noise of single foline according to the propeller and the blade quantity and leaf of the propeller
Prime number measures the thickness and load noise of the propeller；
S305：The average sound pressure level of propeller is calculated according to the thickness and load noise of the propeller.
6. a kind of propeller configurations as claimed in claim 5, which is characterized in that the design of the aircraft with low noise propeller
Step S200 in method is specifically included：
S201：According to the leaf different Reynolds number, the different angles of attack and preset propeller geometric parameter to propeller foline
It is divided, obtains foline group more than two；
S202：To corresponding to velocity coeffficient initial value and each foline group Reynolds number and the angle of attack calculate, obtain each foline group
Corresponding wing aerodynamic coefficient and velocity coeffficient；
S203：It is recycled using optimization algorithm and executes step S202 until convergence, obtains propeller air force data.
7. a kind of propeller configurations as claimed in claim 5, which is characterized in that the design of the aircraft with low noise propeller
Further include after step S100 in method by the leaf corresponding lift coefficient under different Reynolds number and the different angles of attack and
Resistance coefficient embodies in a tabular form.
8. a kind of propeller configurations as claimed in claim 5, which is characterized in that the aircraft flies for small-sized quadrotor
Device.
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| CN106938696B (en) * | 2017-02-20 | 2019-08-13 | 西安爱生技术集团公司 | A kind of sabre type low noise propeller blade design method |
| CN107220412B (en) * | 2017-05-04 | 2020-06-23 | 南京航空航天大学 | Rotor wing thickness noise control method based on variable-area resistance sheet |
| US11008093B2 (en) * | 2018-03-22 | 2021-05-18 | Aurora Flight Sciences Corporation | Systems and methods for reducing the propeller noise |
| CN208149614U (en) * | 2018-04-25 | 2018-11-27 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| US11066189B2 (en) * | 2018-12-07 | 2021-07-20 | The Boeing Company | Flight control system for determining estimated dynamic pressure based on lift and drag coefficients |
| CN109992893A (en) * | 2019-04-03 | 2019-07-09 | 中南大学 | A kind of propeller profile optimization design method |
| CN112487730A (en) * | 2020-10-30 | 2021-03-12 | 南京航空航天大学 | Phase angle control-based multi-rotor aircraft noise suppression method |
| CN113051666B (en) * | 2021-03-25 | 2022-05-31 | 南京航空航天大学 | Noise digital analysis method and system for rotor craft |
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| US5997250A (en) * | 1997-01-09 | 1999-12-07 | Catercopters, Llc | Method and apparatus for controlling pitch of an aircraft propeller |
| KR20090000644A (en) * | 2007-03-14 | 2009-01-08 | 쎄딕(주) | System and method for analyzing flow field and flow noise automatically |
| CN100492375C (en) * | 2007-03-22 | 2009-05-27 | 上海交通大学 | Method for lowering multi-wing centrifugal fan noise |
| CN103530482B (en) * | 2013-11-04 | 2016-11-09 | 东南大学 | Propeller noise Numerical Prediction Method in a kind of nonlinear inflow |
| CN103631994B (en) * | 2013-11-18 | 2017-07-28 | 新疆工程学院 | A kind of method of wind energy conversion system noise radiation law numerical prediction |
| CN104298805B (en) * | 2014-08-13 | 2018-01-12 | 天津大学 | Hypersonic aircraft CFD aerodynamic modeling methods |
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