CN104913896B - A kind of ground experiment analogy method of high-altitude propeller plasma flow control - Google Patents
A kind of ground experiment analogy method of high-altitude propeller plasma flow control Download PDFInfo
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Abstract
The present invention relates to a kind of ground experiment analogy method of high-altitude propeller plasma flow control, comprise the following steps：Calculate the aggregate velocity of the air flow field of each foline, the geometry angle of attack and Reynolds number at the high-altitude propeller blade different radii；Measure and calculate high-altitude propeller Plasma Actuator similar parameter；Make the foline aerofoil profile model for ground wind tunnel experiment；Determine the simulation plasma device structural parameters and excitation power supply parameter of each foline aerofoil profile model；The simulation Plasma Actuator is arranged on each foline aerofoil profile model, the ground wind tunnel experiment of control is flowed by foline aerofoil profile model plasma, lift coefficient, the resistance coefficient of foline aerofoil profile model before and after the simulation Plasma Actuator is opened are gathered, calculated respectively, and flight thrust, moment of torsion, the efficiency of the high-altitude propeller are obtained using foline theoretical calculation.The method of the invention is carried out using conventional ground wind-tunnel, with the advantage such as low cost, generalization be good.
Description
Technical field
The present invention relates to a kind of ground experiment analogy method of high-altitude propeller plasma flow control, and in particular to one
Plant theoretical based on foline, using flow field of the ground routine equipment simulating plasma control propeller under the low air pressure condition of high-altitude
Structure, belongs to aerodynamic experiment field.
Background technology
The spatial domain of near space span ground 20-100 kms.In the low speed near space vehicle master of this spatial domain flight
Will be including stratospheric airship, stratosphere unmanned plane etc., it has important application prospect, domestic granddad in military, civil area
The low speed near space vehicle overwhelming majority for opening report uses propeller as power propulsion system, but due near space
The reason such as air pressure is low, atmospheric density is small, the thrust and efficiency of near space vehicle propeller is very low, many by optimizing spiral shell at present
Revolve oar blade foline configuration, close to space vehicle is improved using methods such as mechanical structure changes propeller, twin screw, collaboration jets
Device propeller performance, with the development of plasma flow control technology, near space vehicle spiral shell is controlled using plasma
Rotation oar turns into a kind of new trend (Numerical study on propeller flow separation control by
DBD plasma aerodynamic actuation, IEEE Transactions on plasma Science, 2013 4
Month, Yufeng Cheng, XuekeChe, WanshengNie).
The theoretical method of propeller performance evaluation mainly has momentum theory, foline theory, vortex theory, piece orderliness
By, whirlpool lattice lift line theory, whirlpool lattice lifting surface theory etc. (air propeller is theoretical, publishing house of BJ University of Aeronautics ＆ Astronautics,
2006, Liu Pei clear), as computing technique develops, numerical value emulation method also turns into a kind of important research method.In experimental study
Aspect, more based on the ratio that advances, the principle of similarity such as Reynolds number is similar, carries out experimental study and (puts down than propeller using contracting in wind-tunnel
Fluid layer dirigible propeller ground wind tunnel test, aviation power journal, in August, 2011, Liu Peiqing, Ma Rong, Zhe in section, Ma Li
River), but for the high-altitude propeller plasma flow control of stratospheric airship, the flash-over characteristic of plasma is received
To having a strong impact on for surrounding environment air pressure, this problem can be solved by being tested in low-density, low-speed wind tunnel, but
Build low-density, low-speed wind tunnel cost it is very high, without generalization, cause the plasma flow carried out at present both at home and abroad
Control release research does not account for this problem, only equips institute and has carried out ground face mould according to free jet reynolds analogue principle
Intend the experimental study that plasma control Airfoil Flow in high-altitude is separate, but also exist not in terms of the similar principle of plasma
Foot.
In sum, the experimental study on plasma flow control is more, but does not account for that plasma is similar to ask
Topic；Stratospheric airship high-altitude propeller experimental study is more, but many using contracting than propeller experimental technique, is only capable of from macroscopical entirety
The performance of upper research propeller；Currently without seeing stratospheric airship high-altitude propeller plasma flow control experimental study
Open report.
The content of the invention
It is an object of the invention to provide a kind of ground experiment analogy method of high-altitude propeller plasma flow control,
Specially in ground routine wind-tunnel by surface dielectric barrier discharge of foline aerofoil profile model of high-altitude propeller blade etc. from
Control release, the experimental technique of simulated altitude propeller surface dielectric barrier discharge plasma flowing control are flowed in daughter.This
Invention methods described is carried out using conventional ground wind-tunnel, with the advantage such as low cost, generalization be good.
The purpose of the present invention is achieved through the following technical solutions：
A kind of ground experiment analogy method of high-altitude propeller plasma flow control, comprises the following steps：
Step 1, several folines are radially divided into by high-altitude propeller blade, theoretical i.e. according to the high-altitude according to foline
The flying height of propeller, flying speed, rotating speed and each foline at propeller blade different radii in high-altitude described in radius calculation
The aggregate velocity of air flow field, the geometry angle of attack and Reynolds number；
Step 2, the structural parameters according to high-altitude propeller Plasma Actuator make actual Plasma Actuator, survey
The parameter in the induction flow field produced when actual Plasma Actuator discharges described in amount still air；
When the excitation power supply of the actual Plasma Actuator is AC power, measures the actual plasma and swash
Encourage the unit length body force of device or the velocity profile of the actual Plasma Actuator induced jet；
When the excitation power supply of the actual Plasma Actuator is high-voltage pulse power source, the actual plasma is measured
The air pressure of body driver working environment and put thermogenetic pressure disturbance；
Step 3, calculates the Plasma Actuator similar parameter at each foline of high-altitude propeller：
When the excitation power supply of the actual Plasma Actuator is AC power, swashed according to the actual plasma
The unit length body force of device or the velocity profile of actual Plasma Actuator induced jet are encouraged, phase is calculated by below equation
Like parameter Rep1、Rep2：
When the excitation power supply of the actual Plasma Actuator is high-voltage pulse power source, according to the actual plasma
The air pressure of body driver working environment and thermogenetic pressure disturbance is put, similar parameter Δ p' is calculated by below equation：
Δ p'=Δs p/p
Wherein, Rep1、Rep2, Δ p' be similar parameter, FLIt is the body force that unit length Plasma Actuator is produced, ρ
It is atmospheric density, μ is air viscosity coefficient, and u is the conjunction of the air flow field of foline at the high-altitude propeller blade different radii
Into speed, UmaxIt is the maximal rate of actual Plasma Actuator induced jet, h0.5For still air plasma is induced
Jet maximal rate halfwidth, i.e. speed are equal to 1/2 point of height apart from wall of maximal rate；Δ p swashs for actual plasma
Encourage device and put thermogenetic pressure disturbance, P is the air pressure of actual Plasma Actuator working environment；
Step 4, the geometry according to foline at the high-altitude propeller blade different radii makes corresponding for ground
The foline aerofoil profile model of face wind tunnel experiment；
Step 5, propeller each foline in high-altitude described in the air pressure, temperature and step 3 according to the ground wind-tunnel
Reynolds number calculates the experiment wind speed of each foline aerofoil profile model；
Step 6, make experiment Plasma Actuator so that the experiment Plasma Actuator similar parameter with it is described
Similar parameter of the actual Plasma Actuator at corresponding foline is equal, obtains simulation of the high-altitude propeller at corresponding foline
Plasma Actuator, determines the structural parameters of the simulation Plasma Actuator at all folines of high-altitude propeller and swashs
Encourage power parameter；
Step 7, each simulation Plasma Actuator is arranged on each corresponding foline aerofoil profile model, by each
The ground wind tunnel experiment of foline aerofoil profile model plasma flowing control, according to the excitation of each simulation Plasma Actuator
Power parameter is discharged, and is gathered respectively, is calculated corresponding foline aerofoil profile mould before and after each simulation Plasma Actuator is opened
The lift coefficient and resistance coefficient of type；
Step 8, according to the lift coefficient and resistance coefficient, the high-altitude propeller is obtained using foline theoretical calculation
Flight thrust, moment of torsion, efficiency.
Further, the synthesis of the air flow field of each foline is fast at the different radii of high-altitude propeller blade described in step 1
Degree refers to the sum velocity of the rotary speed of the air flow field of the foline at the high-altitude propeller pace and the radius；
The geometry angle of attack of the air flow field of each foline refers to described at the different radii of high-altitude propeller blade described in step 1
The angle of attack of the aggregate velocity of the air flow field of each foline at the foline；
The Reynolds number of the air flow field of each foline is with the height at the different radii of high-altitude propeller blade described in step 1
Foline string of the atmospheric density, air viscosity coefficient and the high-altitude propeller blade of empty propeller flying height at the radius
Long and aggregate velocity is calculated for parameter.
Further, step 2 is specially：
Step 2.1, the structural parameters according to high-altitude propeller Plasma Actuator make actual Plasma Actuator,
And identical is closed when the actual Plasma Actuator is placed on into atmospheric density with the high-altitude propeller aloft work
In cabin；
Wherein, the structural parameters of the high-altitude propeller Plasma Actuator refer to the high-altitude propeller plasma excitation
The exposure electrode of device, the width and thickness of implant electrode, the material and thickness of dielectric barrier, the exposure electrode and implantation electricity
Gap of the pole in x directions；
Step 2.2, according to the excitation power supply parameter of the high-altitude propeller plasma excitation device to the actual plasma
Body driver discharges；
When the excitation power supply of the actual Plasma Actuator is AC power, measures the actual plasma and swash
Encourage the unit length body force of device, or the velocity profile for measuring the actual Plasma Actuator induced jet；
When the excitation power supply of the actual Plasma Actuator is high-voltage pulse power source, the actual plasma is measured
The air pressure of body driver working environment and put thermogenetic pressure disturbance.
Further, the chord length of all foline aerofoil profile models is equal in step 4.
Further, it is sharp for the plasma of ground wind tunnel experiment that Plasma Actuator is simulated described in step 6
Encourage device.
Further, step 6 is specially：
Step 6.1, make experiment Plasma Actuator, according in step 2 metering system measurement it is described experiment etc. from
Daughter driver discharged in surface air environment produce induction flow field relevant parameter；
Step 6.2, the experiment wind speed and step 6.1 of the described each foline aerofoil profile model being calculated according to step 5 are measured
The parameter in the induction flow field for obtaining, by the mutually accrued of the Plasma Actuator similar parameter of high-altitude propeller described in step 3
Formula is calculated, the similar parameter at the experiment Plasma Actuator difference foline is calculated；
Wherein, the experiment wind speed of each foline aerofoil profile model replaces foline at the high-altitude propeller blade different radii
Air flow field aggregate velocity；
Step 6.3, when the experiment Plasma Actuator similar parameter with the actual Plasma Actuator in phase
When answering the similar parameter at foline equal, the experiment Plasma Actuator is mould of the high-altitude propeller at corresponding foline
Intend Plasma Actuator；
Step 6.4, the excitation power supply parameter and structural parameters of change experiment Plasma Actuator, repeat step 6.1~
6.3, until it is determined that at all folines of high-altitude propeller simulation Plasma Actuator structural parameters and excitation power supply
Parameter.
Further, in ground wind tunnel experiment described in step 7, the experiment angle of attack of each foline aerofoil profile model and the high-altitude spiral shell
The geometry angle of attack of foline is identical at rotation oar relevant radii.
Further, surface dielectric barrier discharge plasma induction flow field is by surface dielectric barrier discharge plasma
Air-spray or shock wave that driver is produced.
Further, the surface dielectric barrier discharge plasma driver be it is a kind of by atmospherical discharges generation etc. from
The equipment of daughter, is made up of exposure electrode, implant electrode and dielectric barrier, and the exposure electrode and implant electrode are pasted respectively
In the upper and lower surface of the dielectric barrier；The exposure electrode exposes in atmosphere, the high-pressure side phase with the excitation power supply
Connection；The implant electrode is coated with insulating materials, with air exclusion, is connected with ground wire.
Further, the excitation power supply is for surface dielectric barrier discharge plasma driver provides discharge energy
Power supply, can be high-voltage ac power or high-voltage pulse power source；The high-pressure side of the excitation power supply and the plasma excitation
The implant electrode connection of the exposure electrode connection of device, the low-pressure end of excitation power supply and the Plasma Actuator, while ground connection.
Further, the high-altitude refers to the spatial domain more than 1 km apart from ground.
Further, the high-altitude propeller refers to propeller of the flying height more than 1 km.
Further, the ground wind-tunnel is without air pressure adjustment, the ground wind-tunnel of temp regulating function.
Beneficial effects of the present invention are：
The method of the invention is based on foline theory, and propeller is controlled in height using ground routine equipment simulating plasma
Flow field structure under empty low air pressure condition, for studying, assessing flowing control mechanism and effect of the plasma to high-altitude propeller
Really, it utilizes conventional ground wind-tunnel to carry out, with the advantage such as low cost, generalization be good.
Brief description of the drawings
Fig. 1 surface dielectric barrier discharge plasma driver dimensional structure diagrams；
Fig. 2 surface dielectric barrier discharge plasma driver two-dimensional coordinate schematic diagrames；
Fig. 3 propeller foline schematic diagrames；
Fig. 4 propeller foline polygon force analysis schematic diagrames.
Specific embodiment
In order to make the purpose , technical scheme and advantage of the present invention be clearer, below in conjunction with specific embodiment and
Accompanying drawing, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein is only used to explain this
Invention, is not intended to limit the present invention.
The present invention provides a kind of ground experiment analogy method of high-altitude propeller plasma flow control, by following skill
What art scheme was realized：
A kind of ground experiment analogy method of high-altitude propeller plasma flow control, comprises the following steps：
Step 1, several folines are divided into along certain spaced radial by high-altitude propeller blade, are root according to foline theory
According to the flying height of the high-altitude propeller, flying speed, rotating speed and propeller blade different radii in high-altitude described in radius calculation
Locate aggregate velocity, the geometry angle of attack and the Reynolds number of the air flow field of each foline；
Step 2, the structural parameters according to high-altitude propeller Plasma Actuator make actual Plasma Actuator, survey
The parameter in the induction flow field produced when actual Plasma Actuator discharges in amount still air；
When the excitation power supply of the actual Plasma Actuator is AC power, measures the actual plasma and swash
Encourage the unit length body force of device or the velocity profile of the actual Plasma Actuator induced jet；
When the excitation power supply of the actual Plasma Actuator is high-voltage pulse power source, the actual plasma is measured
The air pressure of body driver working environment and put thermogenetic pressure disturbance；
Specifically, one length of structural parameters processing and fabricating according to high-altitude propeller Plasma Actuator it is shorter, its
Its parameter identical Plasma Actuator, actual Plasma Actuator is referred to as by the plasma, by actual plasma
Driver is placed in low pressure vacuum chamber, closes low pressure vacuum chamber, vavuum pump pumping is opened, until in low pressure vacuum chamber
Pressure is reduced to goal pressure, now the air in the atmospheric density in low pressure vacuum chamber and high-altitude propeller real work high-altitude
Density is identical, vavuum pump is closed, then according to the practical power excitation parameters of high-altitude propeller Plasma Actuator to reality
Plasma Actuator applies excitation, and actual Plasma Actuator issues raw electric discharge and produces plasma in high pressure electric excitation,
After discharge stability, or the reaction force that actual Plasma Actuator is produced is measured using dynameter, divided by it is actual etc. from
The unit length body force of actual Plasma Actuator is obtained after daughter driver length, or is surveyed using laser particle image
Fast technology (PIV) measures actual Plasma Actuator induced jet, and actual Plasma Actuator is calculated according to measurement result
The maximal rate and still air Reynolds number of induced jet, or measure actual Plasma Actuator using other e measurement technologies
Induction flow field, the maximal rate and still air Reynolds number of actual Plasma Actuator induced jet are calculated according to measurement result
Or pressure disturbance Δ p and dimensionless perturbation pressure.
The structural parameters of the high-altitude propeller Plasma Actuator are mounted in the plasma on the propeller of high-altitude
The structural parameters of driver.Described structural parameters are the width and thickness of the exposure electrode of Plasma Actuator, implantation electricity
The width and thickness of pole, exposure electrode and implant electrode are in the gap in x directions, the material and thickness of dielectric barrier.
Described low pressure vacuum chamber is to provide highly close with same air density with high-altitude propeller real work
Close cabin.
Described dynameter is the experimental facilities that can accurately measure Plasma Actuator reaction force.
Step 3, calculates the Plasma Actuator similar parameter at each foline of high-altitude propeller：
Unit length body force or actual Plasma Actuator induction according to the actual Plasma Actuator is penetrated
The velocity profile of stream, similar parameter Re is calculated by below equationp1、Rep2：
When in still air, the aggregate velocity of the air flow field of each foline is 0, and phase is calculated by below equation
Like parameter Rep3：
Air pressure according to the actual Plasma Actuator working environment and thermogenetic pressure disturbance is put, passed through
Below equation calculates similar parameter Δ p'：
Δ p'=Δs p/p
Wherein, Rep1、Rep2、Rep3, Δ p' be similar parameter, FLFor the volume that unit length Plasma Actuator is produced
Power, ρ is atmospheric density, and μ is air viscosity coefficient, and u is the air flow field of foline at the high-altitude propeller blade different radii
Aggregate velocity, UmaxIt is the maximal rate of actual Plasma Actuator induced jet, h0.5It is still air plasma
Induced jet maximal rate halfwidth, i.e. speed are equal to 1/2 point of height apart from wall of maximal rate；Δ p is actual plasma
Body driver puts thermogenetic pressure disturbance, and P is the air pressure of actual Plasma Actuator working environment；
Step 4, the geometry according to foline at the high-altitude propeller blade different radii makes corresponding for ground
The foline aerofoil profile model of face wind tunnel experiment, the chord length of all foline aerofoil profile models is equal；
Step 5, propeller each foline in high-altitude described in the air pressure, temperature and step 1 according to the ground wind-tunnel
Reynolds number calculates the experiment wind speed of each foline aerofoil profile model；
Step 6, make experiment Plasma Actuator so that the experiment Plasma Actuator similar parameter with it is described
Similar parameter of the actual Plasma Actuator at corresponding foline is equal, obtains simulation of the high-altitude propeller at corresponding foline
Plasma Actuator, determines the structural parameters of the simulation Plasma Actuator at all folines of high-altitude propeller and swashs
Encourage power parameter；Specially：
Step 6.1, make experiment Plasma Actuator, according in step 2 metering system measurement it is described experiment etc. from
Daughter driver discharged in surface air environment produce induction flow field relevant parameter；
Step 6.2, the experiment wind speed and step 6.1 of the described each foline aerofoil profile model being calculated according to step 5 are measured
The parameter in the induction flow field for obtaining, by the mutually accrued of the Plasma Actuator similar parameter of high-altitude propeller described in step 3
Formula is calculated, the similar parameter at the experiment Plasma Actuator difference foline is calculated；
Wherein, the experiment wind speed of each foline aerofoil profile model replaces foline at the high-altitude propeller blade different radii
Air flow field aggregate velocity；
Step 6.3, when the experiment Plasma Actuator similar parameter with the actual Plasma Actuator in phase
When answering the similar parameter at foline equal, the experiment Plasma Actuator is mould of the high-altitude propeller at corresponding foline
Intend Plasma Actuator；
Step 6.4, the excitation power supply parameter and structural parameters of change experiment Plasma Actuator, repeat step 6.1~
6.3, until it is determined that at all folines of high-altitude propeller simulation Plasma Actuator structural parameters and excitation power supply
Parameter.
Step 7, each simulation Plasma Actuator is arranged on each corresponding foline aerofoil profile model, by each
Foline aerofoil profile model plasma flowing control ground wind tunnel experiment, according to propeller in aloft work blade different radii
The geometry angle of attack and Reynolds number for locating air flow field determine the experiment wind speed and the angle of attack of foline aerofoil profile model, according to each determination
The excitation power supply parameter for simulating Plasma Actuator is discharged, and is gathered respectively, is calculated each simulation plasma excitation
The lift coefficient and resistance coefficient of device corresponding foline aerofoil profile model before and after opening；
Step 8, according to established angle and radius at the corresponding foline of propeller, by the lift coefficient of aerofoil profile model and resistance system
Number is converted into the thrust coefficient and torque coefficient of the foline, by the thrust coefficient and torque coefficient of all folines on whole blade
The total pulling force and total torque that can obtain single paddle are integrated, propeller efficiency is calculated accordingly.
The present invention induces flow field similarity criterion and propeller in aloft work based on surface dielectric barrier discharge plasma
When blade different radii at foline air flow field aggregate velocity, can simulated altitude low air pressure condition following table by testing acquisition
The structural parameters and excitation power supply ginseng of the ground simulation Plasma Actuator in face dielectric barrier discharge plasma induction flow field
Number.
Described surface dielectric barrier discharge plasma induction flow field similarity criterion includes that volume of plasma power is similar
Criterion and plasma heat release similarity criterion.
Described volume of plasma power similarity criterion includes still air Reynolds number, unit length active force similar parameter
With speed amendment jet Reynolds number similar parameter.
Described still air Reynolds number is that the jet Reynolds number based on induced jet maximal rate and jet halfwidth is made
It is similar parameter.
Described unit length active force similar parameter is that have during flowing, and based on driver unit length active force, is flowed
The Reynolds number of speed and dynamic viscosity coefficient.
Described speed amendment jet Reynolds number similar parameter is that have during flowing, based on jet Reynolds number, the maximum speed of jet
The Reynolds number of degree and speed of incoming flow.
Described plasma heat release similarity criterion is dimensionless perturbation pressure #
Δ p'=Δs p/p
Wherein Δ p is that plasma puts thermogenetic pressure disturbance, and P is environmental pressure.
As shown in figure 1, described surface dielectric barrier discharge plasma driver is situated between by the first exposure electrode 1, first
Matter barrier layer 2, the first implant electrode 3 are constituted, and high voltage power supply 4 is applied on the first exposure electrode 1 and the first implant electrode 3, the
One implant electrode 3 is grounded simultaneously.
Described x direction force, as shown in Fig. 2 pointing to the second implant electrode 6 by the second exposure electrode 5, is situated between perpendicular to second
The direction on matter barrier layer 7 is y directions.
The foline theory is that propeller blade is divided into limited length for small section of dr, as shown in figure 3, each is small
Section is referred to as foline, and corresponding chord length is br, the aerodynamic force on each foline is calculated, finally foline aeroperformance is accumulated along blade
Get propeller total aerodynamic force and moment of torsion.
Described propeller aggregate velocity of the air flow field of foline at blade different radii, several in aloft work
What angle of attack and Reynolds number, it is assumed that propeller pace is V0, rotary speed is nsRevolution per second,
Axially distinguish v with ring induced velocityaAnd vt, then it is aggregate velocity on the foline at r away from propeller blade root distanceGeometry angle of attack φr=arctan ((V0+va)/(2πrns-vt)), Reynolds number is Re=ρ
Wrbr/μ.Foline liftResistanceTotal aerodynamic force
CLr、CDrIt is respectively foline lift coefficient and resistance coefficient, ρ is atmospheric density, and μ is air viscosity coefficient.
Propeller foline thrust, rotation torque, absorbed power are respectively dTr=dRrcos(φr+γr), dMr=rsin
(φr+γr)dRr、dPr=2 π rnsdMr.Propeller foline thrust, rotation torque, absorbed power are accumulated to whole blade respectively
Point, you can thrust T, moment of torsion M and the absorbed power P of whole propeller blade are obtained, propeller efficiency is η=TV0/P。
Specifically, the volume of plasma power similarity criterion derivation is as follows：
The surface dielectric barrier discharge plasma body force is that plasma charge is produced under space electric field effect
Body force, the surface dielectric barrier discharge plasma body force is embodied in air force to the control action of free air
Learn in the equation of momentum, i.e., increase a body force source item in the aerodynamics equation of momentum.Because volume of plasma is advocated
To be x direction force, the present invention discusses by taking x direction force as an example, and only consider the region that there is volume of plasma power.As schemed
Shown in 2, the x directions are the directions that implant electrode is pointed to by surface dielectric barrier discharge plasma driver exposure electrode.
The equation of momentum comprising volume of plasma power is as follows：
F in formulaxIt is x directions volume of plasma force densities (N/m3)；
For two similar flow fields, the main similarity transformation formula being related to includes：
(2) formula is substituted into (1) formula, by that can be obtained after arrangement
Here volume of plasma power is primarily upon, makes the similar index before the Section 2 of equation right side be equal to 1, i.e.,
(2) formula is substituted into (4) formula, is obtained
Therefore similar parameter is defined as here
Further to simplify, (6) formula is changed：
μ is dynamic viscosity coefficient in formula.When main flow field meet Reynolds number it is similar when, above formula can be further simplified as：
Because the body force that plasma discharge is produced is a non homogen field, and it is difficult to accurately measure dividing for the volume field of force
Cloth situation, it is contemplated that Fxl2Dimension with N/m, equivalent to the body force that unit length driver is produced, therefore uses unit here
The body force F that length driver is producedLInstead of Fxl2, obtain following similar parameter：
Unit length driver body force FLCan be obtained using two methods.One kind is to use for example micro- power day of dynameter
The direct measurements such as flat, pendulum gear, now can be used (9) formula as similar parameter.Secondly as speed of incoming flow plasma
Discharge process does not produce influence, i.e., speed of incoming flow does not interfere with FL, therefore FLCan be by still air plasma induced jet
X directions velocity profile integration is obtained：
U (y) is x direction speed of the still air plasma induced jet at wall y in formula, and H is still air
The total height of plasma induced jet, h0.5Be still air plasma induced jet maximal rate halfwidth, i.e., it is fast
Degree is equal to 1/2 point of height apart from wall of maximal rate,It is based on h0.5Average speed.
(10) formula is substituted into (9) Shi Ke get：
Further to simplify application, plasma-induced jet maximal rate U can be usedmaxInstead ofCan obtain：
Above formula is the similarity criterion of induced jet in plasma flow control, for still air, carrys out flow velocity
It is 0 to spend, and singular point occurs, and above formula can be dissimilated as：
In sum, the characteristics of its similar parameter of the induced jet of volume of plasma power generation has Reynolds number, therefore
Similar parameter here is defined as Re with reference to the symbol Re of Reynolds numberp, subscript p represents plasma.In still air, can adopt
With the jet Reynolds number based on induced jet maximal rate and jet halfwidth as similar parameter, referred to as still air Reynolds
Number.Have during flowing, if be able to can be used based on the effect of driver unit length with direct measurement driver unit length active force
The Reynolds number of power, speed of incoming flow and dynamic viscosity coefficient is used as similar parameter, referred to as unit length active force similar parameter；Such as
Fruit can measure the velocity profile of induced jet, then can use based on jet Reynolds number, jet maximal rate and speed of incoming flow
Reynolds number is used as similar parameter, referred to as speed amendment jet Reynolds number similar parameter.
Described plasma heat release similarity criterion derivation is as follows：
The plasma heat release is the heat that plasma charge discharges under space electric field effect, the plasma
Heat release is embodied in aerodynamics energy equation to the control action of free air, analyzes plasma from energy equation below
Heat release, and only consider plasma heat release region, the aerodynamics energy equation for containing plasma heat release is as follows：
Q is the heat density (J/m in the unit volume that electric discharge is produced in formula3), its physical quantity scale relation is:
(2), (15) formula are substituted into (14) formula, the similar index before plasma heat release can be obtained after conversion is simultaneously
It is made to be equal to 1：
Further it is transformed to：
In formula bySpecific heat ratio γ can be obtained, then under the conditions of specific heat ratio identical is met, (17) formula can turn
Turn to:
(2), (15) formula are substituted into (18) formula, the similar parameter for obtaining plasma heat release isDue to the distribution of heat
Scope, the regularity of distribution can not possibly accomplish completely similar, also be very difficult to measurement, it is considered to which the unit of Q is J/m3, J/m can be converted into3
=Nm/m3=N/m2=Pa, has identical dimension with pressure, and the main efficacy results of actual plasma heat release are exactly to produce
Pressure disturbance, therefore amount is replaced as Q using pressure disturbance Δ p, therefore similar parameter can be obtainedIt represents immeasurable
Guiding principle perturbation pressure.Because Δ p can gradually change with time, place, can be with two electrode phases of using plasma driver
The maximum pressure pulsation of a certain analogous location in top is reference quantity at neighbour.
Presently preferred embodiments of the present invention is the foregoing is only, is not intended to limit the invention, it is all in essence of the invention
Any modification, equivalent and improvement made within god and principle etc., should be included within the scope of the present invention.
Claims (4)
1. a kind of ground experiment analogy method of high-altitude propeller plasma flow control, it is characterised in that including following step
Suddenly：
Step 1, several folines are radially divided into by high-altitude propeller blade, the high-altitude propeller according to foline theoretical calculation
The aggregate velocity of the air flow field of each foline, the geometry angle of attack and Reynolds number at blade different radii；
Step 2, the structural parameters according to high-altitude propeller Plasma Actuator make actual Plasma Actuator, measure quiet
The parameter in the induction flow field produced when only actual Plasma Actuator discharges described in air；
When the excitation power supply of the actual Plasma Actuator is AC power, the actual Plasma Actuator is measured
Unit length body force or the actual Plasma Actuator induced jet velocity profile；
When the excitation power supply of the actual Plasma Actuator is high-voltage pulse power source, measures the actual plasma and swash
Encourage the air pressure of device working environment and put thermogenetic pressure disturbance；
Step 3, calculates the Plasma Actuator similar parameter at each foline of high-altitude propeller：
Unit length body force or actual Plasma Actuator induced jet according to the actual Plasma Actuator
Velocity profile, similar parameter Re is calculated by below equationp1、Rep2：
Air pressure according to the actual Plasma Actuator working environment and thermogenetic pressure disturbance is put, by following
Formula calculates similar parameter Δ p'：
Δ p'=Δs p/p
Wherein, Rep1、Rep2, Δ p' be similar parameter, FLIt is the body force that the actual Plasma Actuator of unit length is produced, ρ
It is atmospheric density, μ is air viscosity coefficient, and u is the conjunction of the air flow field of foline at the high-altitude propeller blade different radii
Into speed, UmaxIt is the maximal rate of actual Plasma Actuator induced jet, h0.5For still air plasma is induced
Jet maximal rate halfwidth, i.e. speed are equal to 1/2 point of height apart from wall of maximal rate, and Δ p swashs for actual plasma
Encourage device and put thermogenetic pressure disturbance, P is the air pressure of actual Plasma Actuator working environment；
Step 4, the geometry according to foline at the high-altitude propeller blade different radii makes and is used for surface wind accordingly
The foline aerofoil profile model of hole experiment；
Step 5, the air of each foline of high-altitude propeller described in the air pressure, temperature and step 1 according to the ground wind-tunnel
The Reynolds number in flow field calculates the experiment wind speed of each foline aerofoil profile model；
Step 6, makes experiment Plasma Actuator so that the experiment Plasma Actuator similar parameter and the reality
Similar parameter of the Plasma Actuator at corresponding foline is equal, obtain the simulation of high-altitude propeller at corresponding foline etc. from
Daughter driver, determines the structural parameters and excitation electricity of the simulation Plasma Actuator at all folines of high-altitude propeller
Source parameter；
Step 7, each simulation Plasma Actuator is arranged on each corresponding foline aerofoil profile model, by each foline
The ground wind tunnel experiment of aerofoil profile model plasma flowing control, according to the excitation power supply of each simulation Plasma Actuator
Parameter is discharged, and is gathered respectively, is calculated corresponding foline aerofoil profile model before and after each simulation Plasma Actuator is opened
Lift coefficient and resistance coefficient；
Step 8, according to the lift coefficient and resistance coefficient, the flight of the high-altitude propeller is obtained using foline theoretical calculation
Thrust, moment of torsion, efficiency.
2. ground experiment analogy method according to claim 1, it is characterised in that step 2 is specially：
Step 2.1, the structural parameters according to high-altitude propeller Plasma Actuator make actual Plasma Actuator, and will
When the actual Plasma Actuator is placed on atmospheric density with the high-altitude propeller aloft work in identical closed cabin；
Wherein, the structural parameters of the high-altitude propeller Plasma Actuator refer to the high-altitude propeller Plasma Actuator
Exposure electrode, the width and thickness of implant electrode, the material and thickness of dielectric barrier, the exposure electrode and implant electrode
In the gap in x directions；
Step 2.2, according to the excitation power supply parameter of the high-altitude propeller Plasma Actuator to the actual plasma
Driver discharges；
When the excitation power supply of the actual Plasma Actuator is AC power, the actual Plasma Actuator is measured
Unit length body force, or the velocity profile for measuring the actual Plasma Actuator induced jet；
When the excitation power supply of the actual Plasma Actuator is high-voltage pulse power source, measures the actual plasma and swash
Encourage the air pressure of device working environment and put thermogenetic pressure disturbance.
3. ground experiment analogy method according to claim 1, it is characterised in that plasma is simulated described in step 6
Driver is the Plasma Actuator for ground wind tunnel experiment.
4. ground experiment analogy method according to claim 1, it is characterised in that step 6 is specially：
Step 6.1, makes experiment Plasma Actuator, and the experiment plasma is measured according to the metering system in step 2
Driver discharged in surface air environment produce induction flow field parameter；
Step 6.2, experiment wind speed and step 6.1 measurement of the described each foline aerofoil profile model being calculated according to step 5 is obtained
Induction flow field parameter, it is public by the corresponding calculating of the Plasma Actuator similar parameter of high-altitude propeller described in step 3
Formula, calculates the similar parameter at the experiment Plasma Actuator difference foline；
Wherein, the experiment wind speed of each foline aerofoil profile model replaces the sky of foline at the high-altitude propeller blade different radii
The aggregate velocity of airflow field；
Step 6.3, when the experiment Plasma Actuator similar parameter with the actual Plasma Actuator in respective leaves
When similar parameter at element is equal, the experiment Plasma Actuator is the simulation of high-altitude propeller at corresponding foline etc.
Gas ions driver；
Step 6.4, the excitation power supply parameter and structural parameters of change experiment Plasma Actuator, repeat step 6.1~6.3,
Until it is determined that at all folines of high-altitude propeller simulation Plasma Actuator structural parameters and excitation power supply parameter.
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| CN105691596B (en) * | 2016-03-10 | 2018-06-01 | 中国航天空气动力技术研究院 | One species gore office high-altitude propeller |
| CN106679924B (en) * | 2017-02-24 | 2019-08-09 | 中国航天空气动力技术研究院 | A kind of high-frequency induction heating plasma wind-tunnel |
| CN106706262B (en) * | 2017-03-16 | 2018-12-04 | 西北工业大学 | Device for measuring force for the experiment of high-speed wind tunnel plasma flow control |
| CN107238481B (en) * | 2017-05-31 | 2019-06-21 | 西北工业大学 | A kind of aerodynamic characteristics of vehicle analysis method based on plasma |
| CN107631854B (en) * | 2017-10-30 | 2023-06-06 | 吉林大学 | Active control device and control method for plasma boundary layer of model wind tunnel test floor |
| CN110702364B (en) * | 2019-10-22 | 2020-06-30 | 西北工业大学 | High-altitude propeller wind tunnel test data correction method aiming at propeller tip Mach number influence |
| CN110702363B (en) * | 2019-10-22 | 2020-06-30 | 西北工业大学 | High-altitude propeller wind tunnel test data correction method aiming at Reynolds number influence |
| CN115716529B (en) * | 2023-01-10 | 2023-05-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing leading edge drooping dynamic stall control device and method |
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