CN104843173B - Design method of low-noise aircraft propeller - Google Patents
Design method of low-noise aircraft propeller Download PDFInfo
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- CN104843173B CN104843173B CN201510280181.2A CN201510280181A CN104843173B CN 104843173 B CN104843173 B CN 104843173B CN 201510280181 A CN201510280181 A CN 201510280181A CN 104843173 B CN104843173 B CN 104843173B
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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 invention provides a design method of a low-noise aircraft propeller. The design method comprises the following steps: S100, carrying out CFD (computational fluid dynamics) calculation according to the preset basic blade shape of the aircraft propeller, and obtaining corresponding lift coefficients and resistance coefficients of the blade shape at different reynolds numbers and different angles of incidence; S200, carrying out momentum-blade element theory calculation according to the preset environment gas flowing state and propeller geometry parameters, so as to obtain aerodynamic data of the propeller; S300, carrying out FW-H pneumatic acoustic equation calculation according to the preset propeller geometry parameters and the aerodynamic data of the propeller, so as to obtain noise characteristics data of the propeller; and S400, transferring an optimization algorithm based on a simulated annealing strategy, executing the steps S200 to S300 in cycle until converging the noise characteristics data, so as to obtain the optimal geometry parameters of the propeller. According to the design method, the problems of power and noise of the propeller are simultaneously taken into account; and the noise generated by the aircraft in the flight process is greatly lowered.
Description
Technical field
The present invention relates to aircraft field, particularly relate to a kind of method for designing of aircraft with low noise propeller.
Background technology
From the aspect of the Design of Propeller of the small-sized quadrotor of prior art is based primarily upon two: first, design
Propeller lifting resistance characteristic to meet the requirement of quadrotor load-carrying, mobility and power of motor；Second it is ensured that pneumatic
Reduce the work noise of propeller as far as possible on the premise of characteristic.
On domestic and international market, existing Design of Propeller adopts the method for designing of peak efficiency mostly at present, and to noise water
Flat consideration is not enough, and mostly conventional aircraft provides pulling force or thrust, is not almost specifically designed for small-sized quadrotor and sets
The low noise propeller of meter.Quadrotor and conventional propeller used by aircraft are to have substantially in terms of working condition
Difference, therefore, the Design Method of Propeller for quadrotor also needs to study further lifting.
If number of patent application is 201410398306.7, entitled " hypersonic aircraft cfd aerodynamic modeling method "
Patent of invention, successively finally gives through cfd pre-treatment, cfd solver and cfd post processing three phases to after Modeling of Vehicle
The aerodynamic characteristic of aircraft, the design for aircraft provides reliable foundation, and saves development cost.But there is no special pin
There is provided a kind of method for designing that can reduce noise to the propeller of aircraft, and be directed to prior art to obtain propeller gas
Dynamic and noise characteristic and commonly used Fluid Mechanics Computation (computational fluid dynamics, cfd) method, though
So say and can be good at solving fluid mechanics problem with reference to computer hardware computing capability and mathematics numerical computation method, and with
The fast development of Fluid Mechanics Computation (cfd method), its solving result is also more accurate.But its time overhead but allows
People's difficult to accept, especially with propeller continue to optimize development it is desirable to be able to quickly obtain propeller startup and
Using cfd method, noise characteristic, show that pneumatic and noise characteristic starts to meet the demand of people, therefore, it is necessary to provide
A kind of solution cycle that can shorten flight vehicle aerodynamic and noise characteristic, and vehicle spin can be reduced according to solving result
The method of oar noise.
Content of the invention
The technical problem to be solved is: a kind of method for designing of aircraft with low noise propeller is provided, can
Obtain having the aircraft propeller of aerodynamic characteristic and low noise feature concurrently.
In order to solve above-mentioned technical problem, the technical solution used in the present invention is:
A kind of method for designing of aircraft with low noise propeller, comprising:
S100: carry out cfd computational fluid dynamicses calculating according to the substantially leaf of aircraft propeller, obtain described leaf
Corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angle of attack；
S200: according to default environmental gas flow regime, default propeller geometric parameter, and described lift coefficient
Carry out blade momentum theory calculating with resistance coefficient, obtain the air force data of described propeller；
S300: carry out the pneumatic sound of fw-h according to the air force data of default propeller geometric parameter and described propeller
Learn the noise characteristic data that Equation for Calculating obtains propeller；
S400: call the optimized algorithm based on simulated annealing thought to circulate execution step s200 to s300, make an uproar until described
Sound characteristicses Data Convergence, obtains the geometric parameter of propeller.
The beneficial effects of the present invention is: efficient flying quality pursued simply by the aircraft being different from prior art,
And ignore the operating noise pollution that in flight course propeller produces, and then lead to aircraft indoors etc. to have low noise will
The special occasions asked has using limiting, and affects the problem of user flight experience.The present invention provides a kind of aircraft with low noise spiral shell
The method for designing of rotation oar, is first depending on that just fixed propeller is leaf to carry out cfd calculating, obtain just fixed leaf middle different Reynolds number and
Lift coefficient in the case of the different angles of attack and resistance coefficient；Again according to the flowing gas state under specific environment residing for aircraft and
Just fixed leaf geometric parameter carries out the aerodynamic characteristic that blade momentum theory is calculated propeller；Come again, according to expression spiral
The fw-h equation solution of oar noise signal characteristic obtains the noise characteristic of propeller；Finally, call optimization method to propeller
Aerodynamic characteristic, draw the optimal geometric parameters of propeller during noise characteristic and the continuous cycle calculations of just fixed geometric parameter
Number.The propeller configurations obtaining through the method for designing of aircraft with low noise propeller of the present invention, not only ensure that winged
Row device aerodynamic characteristic such as load-carrying, mobility and power in flight course requires；And taken into account noise characteristic, Neng Gouyou simultaneously
Effect reduces the aircraft noise pollution that propeller rotation produces in flight course；Further, optimize the flight of aircraft
Can, the flight experience improving manipulator is it is adaptable to various occasion.
Brief description
Fig. 1 is a kind of FB(flow block) of the method for designing of present invention aircraft with low noise propeller；
Fig. 2 is a kind of FB(flow block) of the method for designing of present invention aircraft with low noise propeller；
Fig. 3 is a kind of FB(flow block) of the method for designing of present invention aircraft with low noise propeller.
Specific embodiment
By describing the technology contents of the present invention in detail, being realized purpose and effect, below in conjunction with embodiment and coordinate attached
Figure is explained.
The design of most critical of the present invention is: carries out cfd calculating and blade momentum according to default propeller is substantially leaf
Theoretical Calculation obtains the aerodynamic characteristic of propeller, then passes through fw-h calculated propeller acoustic characteristic, finally combines simulation
Annealing optimisation algorithm obtains the optimal geometrical parameter of propeller.
Explanation of nouns:
Cfd: computational fluid dynamicses；With electronic computer as instrument, apply the mathematical method of various discretizations, convection cell
All kinds of problems of mechanics carry out numerical experiment, computer mould fits analysis and research, to solve various practical problems；
Fw-h equation: aeroacoustics equation；
Reynolds number: a kind of can be used to characterize the dimensionless number of flow of fluid situation, the stream of fluid can be distinguished using Reynolds number
Dynamic is laminar flow or turbulent flow it is also possible to determining that object flows suffered resistance in a fluid；
The angle of attack: for fixed wing airplane, the direction of advance (being equivalent to the direction of air-flow) of wing and wing chord are (with fuselage axis
Different) angle the angle of attack, the also referred to as angle of attack, it is to determine benchmark, lift coefficient and the resistance system of wing attitude in the gas flow
Number is all the function of the angle of attack, and in certain limit, the angle of attack is bigger, and lift coefficient is also bigger with resistance coefficient；
Lift coefficient: a characteristic, refer to lift suffered by object and air-flow dynamic pressure and area of reference product it
Than；
Resistance coefficient: for aircraft, resistance coefficient be defined as resistance suffered by object (as aircraft, guided missile) with
Air-flow dynamic pressure and the ratio of area of reference, are characteristics；
Propeller geometric parameter: the diameter d of inclusion propeller, blade number b, solidity σ, blade angle beta, geometrical pitch h, reality
The propeller configurations parameter of border pitch hg and theoreticalpiston ht；
Foline: blade is made up of the unlimited number of blade continuously arranged micro- section (i.e. foline)；
Convergence: a kind of offline mode of aircraft, the first half of expansion big gun jet pipe is from large to small to middle shrinkage to one
Narrow larynx.Change from small to big after narrow larynx again and expand outwardly.Combustion gas is subject to the first half of high pressure flow nozzle, through after narrow larynx by latter half of
Effusion
Air force data: the data being collected based on aerodynamic；
Noise characteristic data: the data being collected based on noise characteristic in flight course for the aircraft；
Wing aerodynamic coefficient: the coefficient based on wing aerodynamic features, refer to the air force of three-dimensional wing
Coefficient, with the Changing Pattern of wing geometric shape, head on free stream Mach number, the angle of attack and yaw angle, is to determine that flight air force is special
The most important factor of property；
Velocity coeffficient initial value: flight speed in flight course for the aircraft is initial with the ratio of the speed of air velocity
Value；
Velocity coeffficient: the ratio of flight speed in flight course for the aircraft and the speed of air velocity；
Time-derivative: how to determine the instantaneous rate of change of functional value during expression Functions in Time Domain independent variable change；
Load noise: aircraft run in the air and on the ground and transportation in, the statistics of the noise that structure is born
Represent.
Refer to Fig. 1 and Fig. 2, the present invention provides a kind of method for designing of aircraft with low noise propeller, comprising:
S100: substantially leaf according to default aircraft propeller carries out cfd computational fluid dynamicses calculating, obtains institute
State leaf corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angle of attack；
S200: according to default environmental gas flow regime, default propeller geometric parameter, and described lift coefficient
Carry out blade momentum theory calculating with resistance coefficient, obtain the air force data of described propeller；
S300: carry out the pneumatic sound of fw-h according to the air force data of default propeller geometric parameter and described propeller
Learn the noise characteristic data that Equation for Calculating obtains propeller；
S400: call the optimized algorithm based on simulated annealing thought to circulate execution step s200 to s300, make an uproar until described
Sound characteristicses Data Convergence, obtains the geometric parameter of propeller.
Knowable to foregoing description, the beneficial effects of the present invention is: the present invention provides a kind of aircraft with low noise propeller
Method for designing, be first depending on that just fixed propeller is leaf to carry out cfd calculating, obtain just fixed leaf middle different Reynolds number and difference
Lift coefficient in the case of the angle of attack and resistance coefficient；Again according to the flowing gas state under specific environment residing for aircraft and just calmly
Leaf geometric parameter carries out the aerodynamic characteristic that blade momentum theory is calculated propeller；Come again, make an uproar according to expression propeller
The fw-h equation solution of acoustical signal characteristic obtains the noise characteristic of propeller；Finally, call optimization method in the gas to propeller
The optimal geometrical parameter of propeller is drawn during dynamic characteristic, noise characteristic and the continuous cycle calculations of just fixed geometric parameter.
The propeller configurations obtaining through the method for designing of aircraft with low noise propeller of the present invention, not only ensure that aircraft
In flight course, the aerodynamic characteristic such as load-carrying, mobility and power requires；And taken into account noise characteristic simultaneously, can effectively drop
The noise pollution that propeller rotation produces in flight course of low aircraft；Further, optimize the flying quality of aircraft, carry
The flight experience of high manipulator is it is adaptable to various occasion.
Further, step s200 specifically includes:
S201: according to described leaf different Reynolds number, the different angles of attack and default propeller geometric parameter to propeller
Foline is divided, and obtains foline group more than two；
S202: the Reynolds number corresponding to velocity coeffficient initial value and each foline group and the angle of attack are calculated, obtains each leaf
Element organizes corresponding wing aerodynamic coefficient and velocity coeffficient；
S203: using optimized algorithm circulation execution step s202 until convergence, obtain propeller air force data.
Further, step s300 specifically includes:
S301: according to the foline aerodynamic parameter in the air force data of propeller, the geometry number of described propeller
According in propeller radius, rotating speed and observer's position coordinateses be iterated calculating, obtain time delay and relative position vector；
S302: carry out fw-h aeroacoustics Equation for Calculating according to described time delay and relative position vector, obtain f, m, relatively
The time-derivative answered and relative position vector direction projection amount；
S303: be calculated thickness and the load of the single foline of described propeller using fw-h aeroacoustics Equation Approximate
Lotus noise；
S304: according to the thickness of the single foline of described propeller and the blade quantity of load noise and described propeller
Obtain thickness and the load noise of described propeller with foline quantity；
S305: be calculated the average sound pressure level of propeller according to the thickness of described propeller and load noise.
Further, also include described leaf corresponding liter under different Reynolds number and the different angle of attack after step s100
Force coefficient and resistance coefficient embody in a tabular form.
Further, described aircraft is small-sized quadrotor.
Refer to Fig. 2 and Fig. 3, embodiments of the invention one are:
S100: substantially leaf according to default aircraft propeller carries out cfd computational fluid dynamicses calculating, obtains institute
State leaf corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angle of attack；
Substantially leaf by pre-set flight device propeller, obtain and calculate basis；
S101: by described leaf under different Reynolds number and the different angles of attack corresponding lift coefficient and resistance coefficient with table
Case form embodies.
S200: according to default environmental gas flow regime, default propeller geometric parameter, and described lift coefficient
Carry out blade momentum theory calculating with resistance coefficient, obtain the air force data of described propeller；
Described default environmental gas flow regime refers to the environment residing for a default aircraft, such as indoor environment, room
Rainy day environment of external environment, outdoor strong wind atmosphere or outdoor etc., each environment has corresponding specific environment gas
Flow regime；Calculated by combining, obtain the pneumatic spy under this specific environment gas circulation status for the propeller of aircraft
Property, provide operating basis for subsequent calculations.
Specifically include:
S201: according to described leaf different Reynolds number, the different angles of attack and default propeller geometric parameter to propeller
Foline is divided, and obtains foline group more than two；
S202: the Reynolds number corresponding to velocity coeffficient initial value and each foline group and the angle of attack are calculated, obtains each leaf
Element organizes corresponding wing aerodynamic coefficient and velocity coeffficient；
S203: using optimized algorithm circulation execution step s202 until convergence, obtain propeller air force data.
S300: carry out the pneumatic sound of fw-h according to the air force data of default propeller geometric parameter and described propeller
Learn the noise characteristic data that Equation for Calculating obtains propeller；
Specifically include:
S301: according to the foline aerodynamic parameter in the air force data of propeller, the geometry number of described propeller
According in propeller radius r, rotating speed q and observer's position coordinateses be iterated calculate, obtain time delay and relative position vector；
S302: carry out fw-h aeroacoustics Equation for Calculating according to described time delay and relative position vector, obtain f, m, relatively
The time-derivative answered and relative position vector direction projection amount；
S303: be calculated thickness and the load of the single foline of described propeller using fw-h aeroacoustics Equation Approximate
Lotus noise；
S304: according to the thickness of the single foline of described propeller and the blade quantity of load noise and described propeller
Obtain thickness and the load noise of described propeller with foline quantity；
S305: be calculated the average sound pressure level of propeller according to the thickness of described propeller and load noise.
S400: call the optimized algorithm based on simulated annealing thought to circulate execution step s200 to s300, make an uproar until described
Sound characteristicses Data Convergence, obtains the optimal geometrical parameter of propeller.In sum, a kind of aircraft with low noise that the present invention provides
The propeller configurations that the method for designing of propeller obtains, not only ensure that aircraft load-carrying, mobility and work(in flight course
The aerodynamic characteristics such as rate require；And taken into account noise characteristic simultaneously, can effectively reduce aircraft propeller in flight course
The noise pollution that rotation produces；Further, optimize aircraft flying quality, improve manipulator flight experience it is adaptable to
Various occasions.
The foregoing is only embodiments of the invention, not thereby limit the present invention the scope of the claims, every using this
The equivalents that bright description and accompanying drawing content are made, or directly or indirectly it is used in the technical field of correlation, all include in the same manner
In the scope of patent protection of the present invention.
Claims (4)
1. a kind of method for designing of aircraft with low noise propeller is it is characterised in that include:
S100: substantially leaf according to default aircraft propeller carries out cfd computational fluid dynamicses calculating, obtains described leaf
Shape corresponding lift coefficient and resistance coefficient under different Reynolds number and the different angle of attack；
S200: according to default environmental gas flow regime, default propeller geometric parameter, and described lift coefficient and resistance
Force coefficient carries out blade momentum theory calculating, obtains the air force data of described propeller；
S300: the air force data according to default propeller geometric parameter and described propeller carries out fw-h aeroacoustics side
Journey is calculated the noise characteristic data of propeller；
S400: call the optimized algorithm based on simulated annealing thought to circulate execution step s200 to s300, until described noise is special
Property Data Convergence, obtains the geometric parameter of propeller；
Step s200 specifically includes:
S201: according to described leaf different Reynolds number, the different angles of attack and default propeller geometric parameter to propeller foline
Divided, obtained foline group more than two；
S202: the Reynolds number corresponding to velocity coeffficient initial value and each foline group and the angle of attack are calculated, obtains each foline group
Corresponding wing aerodynamic coefficient and velocity coeffficient；
S203: using optimized algorithm circulation execution step s202 until convergence, obtain propeller air force data.
2. a kind of method for designing of aircraft with low noise propeller according to claim 1 is it is characterised in that step s300
Specifically include:
S301: according to the foline aerodynamic parameter in the air force data of propeller, the geometry of described default propeller
Propeller radius in data, rotating speed and observer's position coordinateses are iterated calculating, and obtain time delay and relative position vector；
S302: carry out fw-h aeroacoustics Equation for Calculating according to described time delay and relative position vector, obtain the corresponding time
Derivative and relative position vector direction projection amount；
S303: be calculated the thickness of the single foline of described propeller using fw-h aeroacoustics Equation Approximate and load is made an uproar
Sound；
S304: according to the thickness of the single foline of described propeller and the blade quantity of load noise and described propeller and leaf
Prime number measures thickness and the load noise of described propeller；
S305: be calculated the average sound pressure level of propeller according to the thickness of described propeller and load noise.
3. a kind of method for designing of aircraft with low noise propeller according to claim 1 is it is characterised in that step s100
Also include afterwards by described leaf under different Reynolds number and the different angles of attack corresponding lift coefficient and resistance coefficient with form shape
Formula embodies.
4. a kind of method for designing of aircraft with low noise propeller according to claim 1 is it is characterised in that described flight
Device is small-sized quadrotor.
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| CN201510280181.2A CN104843173B (en) | 2015-05-27 | 2015-05-27 | Design method of low-noise aircraft propeller |
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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 |
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| CN103530482A (en) * | 2013-11-04 | 2014-01-22 | 东南大学 | Method for forecasting noise value of propeller in uneven inflow |
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