CN107525647B - A kind of dynamical bifurcation generating device of aerodynamic stalling - Google Patents
A kind of dynamical bifurcation generating device of aerodynamic stalling Download PDFInfo
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- CN107525647B CN107525647B CN201710619568.5A CN201710619568A CN107525647B CN 107525647 B CN107525647 B CN 107525647B CN 201710619568 A CN201710619568 A CN 201710619568A CN 107525647 B CN107525647 B CN 107525647B
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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Abstract
The present invention discloses a kind of dynamical bifurcation generating device of aerodynamic stalling, and setting exhibition is connect by angular displacement sensor with braced frame top surface sliding block to host wing model to be measured along the vertical direction, taper shaft in braced frame；Root shaft is connect with braced frame bottom surface slipper bearing；Make host wing model to be measured that there is front-rear direction one-movement-freedom-degree and the rotational freedom around vertical direction.Angle of attack adjustment structure is designed simultaneously and adjusts the host wing angle of attack to be measured, and sink-float regulating mechanism adjusts host wing model sink-float rigidity to be measured；The pressure sensor of the angular displacement sensor for the angle that measurement host wing rotate around vertical direction, the dynamic pressure numerical value of measurement host wing surface is also equipped on host wing to be measured；The PIV measuring device of measurement flow field characteristic is installed in braced frame.The verifying to dynamical bifurcation Numerical Simulation Results caused by aerodynamic stalling can be achieved in the present invention, and provides amendment for theoretical modeling, proposes the practicable strategy for increasing dynamical bifurcation speed with this.
Description
Technical field
The invention belongs to aviation aircraft design and wind energy conversion system fields, are that a kind of dynamical bifurcation of aerodynamic stalling fills
It sets, specifically one kind is directed to Fixed Wing AirVehicle wing, rotor craft rotor, pneumatic equipment bladess generation aerodynamic stalling
The experimental system of its dynamic response and dynamical bifurcation is measured afterwards.
Background technique
When the wing angle of attack is larger, aerodynamic force can separate actual aircraft from aerofoil surface, when separation reaches certain journey
Degree, aerodynamic force can be reduced suddenly, and this phenomenon is referred to as aerodynamic stalling.Airfoil lift reduces after aerodynamic stalling, and the angle of attack reduces,
Air-flow adheres to again, and lift increases, and repeatedly, self-sustained oscillation occurs for pitching on structure pitch freedom.It is this due to gas
Dynamical bifurcation caused by dynamics stall is also commonly referred to as stall flutter, is a kind of serious aeroelasticity wild effect.Great Zhan string
It is more larger since wing tip deforms than wing, especially solar powered aircraft, wing tip can be made to be in a very big angle of attack, be easy to make its hair
Angry dynamics stall, and then cause dynamical bifurcation, serious destruction will be caused when serious to body.In addition lifting airscrew and spiral
Dynamical bifurcation situation can also occur for paddle.The propeller rotated just will appear aerodynamic stalling when the angle of attack increases to stall zone
Dynamical bifurcation.It is not dependent on the characteristic condition of the classical flutter such as inertia force, elastic force and aerodynamic force, crucial
It is because aerodynamic force issues angry dynamics stall in big situations of attack and causes, is that a kind of more complicated nonlinear kinetics is existing
As.
In general, when the angle of attack reaches the range of stall, the characteristics of can showing is that aerodynamic force starts to send out in aerofoil surface
It is estranged from after separation reaches a certain level, lift brought by aerodynamic force sharply declines, and acts on the restoring force on wing
The wing angle of attack will be made to become smaller, air-flow is attached to aerofoil surface since the angle of attack becomes smaller again, restores the lift of wing, so past
Multiple, in pitch orientation vertical dip mining occurs for wing.Aerodynamic stalling is occurring, wing enters after vertical dip mining state, different
The amplitude of speed of incoming flow, vertical dip mining is different.It is often the case that vertical dip mining occurs suddenly under a certain speed for wing, and do not receive
It holds back, increases when with speed of incoming flow, a variety of variations, referred to as dynamical bifurcation phenomenon, this phenomenon master can be presented in vertical dip mining amplitude
Caused by if the aerodynamic force as caused by aerodynamic force stall is non-linear.
The mechanism of dynamical bifurcation caused by research aerodynamic force stall at present is also mainly based on numerical simulation, but due to gas
The process of power separation and stall is sufficiently complex, and unsteady aerodynamic force simulates the uncertainty assumed, aircaft configuration parameter not
Certainty, numerical simulation are needed by verification experimental verification.Invention dynamical bifurcation generating device is needed, it can be with quantitative study aerodynamic force stall
The condition and influence factor that caused dynamical bifurcation occurs, and after diverging wing structure response condition, provide
Reliable experimental condition, to find out inhibition by laboratory facilities or improve the effective means of dynamical bifurcation speed.
The simulation to wing stall flutter is realized in wind-tunnel, be primarily present following problems:
1. dynamical bifurcation characteristic and the initial angle of attack of wing and equilbrium position there are much relations, the adjustable initial angle of attack how is designed
With balance position mechanism and its measuring mechanism.
2. the main reason for as dynamical bifurcation, unsteady aerodynamic force dynamic characteristic measuring is more multiple when aerodynamic force stall
Miscellaneous, stall event is difficult to happen, and the dynamic variation characteristic of aerodynamic force is also not easy to capture.
Based on the above situation, it is necessary to propose that one kind can accurately generate the dynamical bifurcation phenomenon of wing aerodynamic power stall
Experimental rig and method, to provide reference for correlative study.
Summary of the invention
In view of the above-mentioned problems, the invention proposes a kind of dynamical bifurcation device of aerodynamic stalling, application is to be directed to
There may be the aircraft of aerodynamic stalling dynamical bifurcation phenomenon, gyroplane and wind energy conversion system can produce and caused by aerodynamic force stall
Dynamical bifurcation phenomenon, and unsteady aerodynamic force dynamic characteristic and wing dynamic response are measured, are used for exploratory flight device
Or pneumatic equipment bladess dynamical bifurcation characteristic.
Host wing model to be measured is arranged in the dynamical bifurcation generating device of aerodynamic stalling of the present invention inside braced frame, to
It surveys host wing model to open up to along the vertical direction, taper shaft is connected by angular displacement sensor with the sliding block of braced frame top surface.
Root shaft is connected by bearing with the sliding block of braced frame bottom surface；Make host wing model to be measured with movement along the longitudinal direction
Freedom degree, and the rotational freedom around vertical direction.The angle of attack of host wing to be measured is adjusted by angle of attack regulating mechanism, master to be measured
The sink-float rigidity of wing model is adjusted by sink-float regulating mechanism.
It is also equipped on host wing to be measured for measuring angular displacement, the measurement host wing table that host wing is rotated around vertical direction
The pressure sensor of the dynamic pressure numerical value in face.PIV measurement dress for measuring flow field characteristic is installed in braced frame simultaneously
It sets.
When being tested, the initial angle of attack of host wing model to be measured is adjusted by pitching adjusting mechanism, and is adjusted to be measured
The sink-float rigidity of host wing model, which reaches, requires rigidity.Then increase wind speed and stablize and be worth at one, measure under the flow velocity
The dynamic response characteristic of flow field characteristic, aerofoil surface Pneumatic pressure characteristic and wing passes through phenomenon and structure, pneumatic gauging number
It is judged that dynamic stall characteristic and dynamical bifurcation characteristic；And by changing wind speed, the dynamical bifurcation characteristic under different wind speed is measured.
The present invention has the advantages that
1, the dynamical bifurcation generating device of aerodynamic stalling of the present invention, ground in face of the dynamical bifurcation as caused by aerodynamic stalling into
Row simulates the verifying, it can be achieved that dynamical bifurcation Numerical Simulation Results caused by aerodynamic stalling, and provides amendment for theoretical modeling,
The practicable strategy for increasing dynamical bifurcation speed is proposed with this, and there is important practical value.
2, in the dynamical bifurcation generating device of aerodynamic stalling of the present invention, for controlling the spring of wing pitching and the rigidity that rises and falls
Group and initial angle regulating device can be replaced, rigid convenient for the different initial angles of attack and different torsions and sink-float is arranged
Degree, for studying the factor for influencing aerodynamic force stall and dynamical bifurcation spot speed.
3, the dynamical bifurcation generating device of aerodynamic stalling of the present invention, favorable repeatability, strong operability, cost are relatively low
It is honest and clean, and easy to operate, application easy to spread is installed, the dynamical bifurcation for being highly suitable for generating under aerodynamic force stall condition is existing
As, and measure critical data.
4, the dynamical bifurcation generating device of aerodynamic stalling of the present invention can be used for binary wing panel, wing, high aspect ratio flight
The dynamical bifurcation characteristic research of the aerodynamic force stall of each class formation such as device wing, large fan.
Detailed description of the invention
Fig. 1 is the dynamical bifurcation generating device overall structure diagram of aerodynamic stalling of the present invention.
In figure:
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
The dynamical bifurcation generating device of aerodynamic stalling of the present invention, including braced frame 1, sliding equipment 2, angle of attack regulating mechanism
3, rise and fall regulating mechanism 4, linear acceleration transducer 5, angular displacement sensor 6, pressure sensor 7, PIV measuring device 8 and signal
Monitoring processing system 9, as shown in Figure 1.
Bracket of the braced frame 1 as dynamical bifurcation generating device of the present invention is cube structure.Braced frame 1
Top surface and bottom surface are the mounting surface of sliding equipment 2, are equipped with a set of sliding equipment 2 in an identical manner respectively.Sliding equipment 2 wraps
Include two crossbeams 201 along the setting of 1 left and right directions of braced frame, a sliding rail 202 along the setting of 1 front-rear direction of braced frame；
Sliding rail 202 is installed between two crossbeams 201, and the center of sliding rail 202 is located at 1 end face center of braced frame；It is sliding on the sliding rail 202
It is dynamic that sliding block 203 is installed.
Host wing model 10 to be measured, host wing to be measured are installed between sliding equipment 2 on above-mentioned 1 top surface of braced frame and bottom surface
Model 10 is made of the covering that host wing skeleton is laid with host wing skeleton outer wall.Host wing model 10 to be measured is opened up to along vertical side
To at 1 center of braced frame.The taper shaft of host wing model 10 to be measured is fixed on support by angular displacement sensor 6
On sliding block in 1 top surface sliding equipment 2 of frame；Root shaft is directly mounted at 1 bottom surface sliding equipment 2 of braced frame by bearing
In sliding block on.Make host wing model 10 to be measured with one-movement-freedom-degree along the longitudinal direction as a result, and around vertical direction
Rotational freedom；It is changed with time by the angle of attack that angular displacement sensor 6 can measure host wing.The tip of host wing model to be measured
Linear acceleration transducer 5 is also pasted in portion's shaft, for measuring host wing sink-float acceleration.
The angle of attack regulating mechanism 3 has two sets, is located on a cross section of 1 top of braced frame and lower part.
Two sets of angle of attack regulating mechanisms 3 are made of 301, four angle of attack adjustment springs 302 of swing arm with two adjusters 303.Wherein, it is located at
In the angle of attack regulating mechanism 3 on 1 top of braced frame: the taper that 301 center of swing arm is fixedly sheathed in host wing model 10 to be measured turns
On axis.Enabling four angle of attack adjustment springs 302 is respectively the angle of attack adjustment spring A, B, C, D；Two adjusters 303 use gaily decorated basket spiral shell
Silk, respectively adjuster A and B；By being connected on front side of angle of attack adjustment spring A and braced frame 1 on front side of 301 left end of swing arm, swing arm
It is connected by angle of attack adjustment spring B with adjuster A on rear side of 301 left ends, is connected on rear side of adjuster A and braced frame 1；And angle of attack tune
Section spring A, angle of attack adjustment spring B and adjuster A are coaxial, and axis is located on 1 left side of braced frame.On front side of 301 right end of swing arm
It is connected by angle of attack adjustment spring C with adjuster B, is connected on front side of adjuster B and braced frame 1；Pass through on rear side of 301 right end of swing arm
It is connected on rear side of spring D and braced frame 1；Same angle of attack adjustment spring C, angle of attack adjustment spring D and adjuster B are coaxial, axis position
In on 1 right side of braced frame.Angle of attack regulating mechanism 3 positioned at 1 lower part of braced frame and the angle of attack positioned at 1 top of braced frame
The mounting means of regulating mechanism 3 is identical.In above-mentioned angle of attack regulating mechanism 3, angle of attack adjustment spring 302 controls machine to be measured for providing
The rigidity of wing model angle of attack direction freedom degree makes four adjusters, 303 elongation phase by being adjusted in synchronism four adjusters 303
Together, and then equal length stretches angle of attack adjustment spring, realizes that the angle of attack of host wing model to be measured is adjusted.
The sink-float regulating mechanism 4 is two sets, is respectively arranged in 1 top of braced frame and lower part；Sink-float regulating mechanism 4 be
Two sink-float adjustment springs are constituted；Wherein, in the sink-float regulating mechanism 4 on 1 top of braced frame, two sink-float adjustment spring difference
Positioned at 10 taper shaft opposite side of host wing model to be measured, one end is connected with 10 taper shaft of host wing model to be measured, the other end point
It is not connected with 1 front and back side of braced frame；And two sink-float adjustment springs are coaxial, axis is located at the adjusting of the 1 top angle of attack of braced frame
On 3 place cross section of mechanism.The sink-float regulating mechanism 4 of the sink-float regulating mechanism 4 and 1 top of braced frame of 1 lower part of braced frame
Mounting means is identical, and 4 axis of sink-float regulating mechanism of 1 lower part of braced frame is located at braced frame lower part angle of attack regulating mechanism 3
On the cross section of place.The sink-float stiffness characteristics of host wing are adjusted by two sets of sink-float regulating mechanisms 4 as a result,.
The pressure sensor 7 is installed on host wing model to be measured using the dynamic pressure transducer of unsteady aerodynamic force
Inside 10, and it is located at 10 middle part of host wing model to be measured.It is provided with pressure tap 11 on 10 middle part wall surface of host wing model to be measured simultaneously,
For installing pressure-measuring pipe, pressure-measuring pipe one end connects pressure sensor 7, is connected to outside the other end and host wing model 10 to be measured；It is logical
Over-voltage force snesor 7 can measure the dynamic pressure numerical value of host wing surface, real-time display aerodynamic stalling characteristic.
The transmitting terminal of the PIV measuring device 8 is installed on 1 left side wall of braced frame, towards host wing model 10 to be measured,
Laser can be emitted in left-right direction.The receiving end of PIV measuring device 8 is installed on 1 bottom surface of braced frame, towards host wing mould to be measured
Type 10 receives the formation image returned along the vertical direction.
Above-mentioned linear acceleration transducer 5, angular displacement sensor 6, pressure sensor 7, the receiving end of PIV measuring device 8 are equal
It is connected with signal monitoring processing system 9, measuring signal can be sent to signal monitoring processing system 9 and handled.
When the dynamical bifurcation generating device of aerodynamic stalling is tested through the invention, the specific steps are as follows:
Step 1: by using suitable angle of attack adjustment spring 302, and adjusting adjuster, realize to spring rate
It is adjusted with the initial angle of attack of the adjusting of tensile elongation, and then realization wing model 10 to be measured；Angular displacement sensor 6 in the above process
The initial angle of attack of real-time measurement host wing model 10 to be measured, until the initial angle of attack of host wing model 10 to be measured reaches measurement request
Angle.
Step 2: by using suitable sink-float adjustment spring, the sink-float rigidity for adjusting host wing model 10 to be measured is reached
It is required that rigidity.
Step 3: adjusting the transmitting end position of PIV measuring device 8, cut it towards the host wing for needing to measure flow field characteristic
Face.The measurement direction of linear acceleration transducer 5 is adjusted simultaneously to rise and fall direction towards host wing model 10 to be measured.
Step 4: wind-tunnel booting, incoming flow passes through aerofoil, to steady air current.
Step 5: the dirty field characteristic of current air velocity being measured by PIV measuring device 8, host is measured by pressure sensor 7
Wing surface dynamic pressure characteristic, by angular displacement sensor 6 measure host wing rotated around vertical direction angular displacement, by linear acceleration
Sensor 5 measures host wing along the displacement of the lines characteristic of 202 track of sliding rail, is stored in signal monitoring processing system 9, observation experiment
Phenomenon.
Step 6: increasing wind speed, repeat step 5 experiment, when wind speed reaches dynamical bifurcation speed, aerofoil starts pitching vibration
It swings；
Through the above steps 1 ~ 6, dynamic stall characteristic and dynamic are judged eventually by phenomenon and structure, pneumatic gauging data
Dynamical bifurcation characteristic under Bifurcation Characteristics, and the different wind speed of measurement.
After one group of experiment is completed, return step 1 adjusts wing model to be measured to the new initial angle of attack, carries out different
Dynamical bifurcation experiment under state.
Claims (5)
1. a kind of dynamical bifurcation generating device of aerodynamic stalling, it is characterised in that: host wing to be measured is set inside braced frame
Model, host wing model to be measured are opened up to along the vertical direction, and taper shaft passes through the cunning of angular displacement sensor and braced frame top surface
Block is connected；Root shaft is connected by bearing with the sliding block of braced frame bottom surface；There is host wing model to be measured along front and back
To one-movement-freedom-degree, and the rotational freedom around vertical direction；The angle of attack of host wing to be measured passes through angle of attack regulating mechanism tune
Section, the sink-float rigidity of host wing model to be measured are adjusted by sink-float regulating mechanism；
The angle of attack regulating mechanism is located at top and lower position in braced frame；Angle of attack regulating mechanism, which has, is installed on master to be measured
Swing rod and swing rod both ends in wing model shaft are equipped with coaxial two springs and an adjuster；Two spring positions
In swing rod opposite side, one end is connect with swing rod, and the other end is separately connected braced frame and adjuster, adjuster and braced frame phase
Even；The adjuster at swing rod both ends is located at swing rod opposite side simultaneously；By being adjusted in synchronism top and the tune in lower section angle of attack regulating mechanism
Device is saved, realizes the synchronous adjustment of spring elongation length, and then realize the adjusting of host wing Model angle of attack to be measured；Above-mentioned top is under
The angle of attack regulating mechanism of side is located above braced frame and on two cross sections of lower section；
It is also equipped on host wing to be measured for measuring angular displacement sensor, the measurement host wing that host wing is rotated around vertical direction
The pressure sensor of the dynamic pressure numerical value on surface；PIV measurement for measuring flow field characteristic is installed in braced frame simultaneously
Device.
2. a kind of dynamical bifurcation generating device of aerodynamic stalling as described in claim 1, it is characterised in that: sink-float regulating mechanism is
Two sets, it is respectively arranged in braced frame top and lower part, is made of two coaxial sink-float adjustment springs；Two sink-floats adjust bullet
Spring is located at host wing model shaft opposite side to be measured, and one end is connected with host wing model shaft to be measured, the other end respectively with support frame
Frame is connected.
3. a kind of dynamical bifurcation generating device of aerodynamic stalling as described in claim 1, it is characterised in that: pressure sensor installation
In in host wing model to be measured, and it is located in the middle part of host wing model to be measured；It is provided on host wing model middle wall face to be measured simultaneously
Pressure tap, installs pressure-measuring pipe in pressure tap, and pressure-measuring pipe one end connects pressure sensor, outside the other end and host wing model to be measured
Connection.
4. a kind of dynamical bifurcation generating device of aerodynamic stalling as described in claim 1, it is characterised in that: PIV measuring device
Transmitting terminal is installed on braced frame side wall, towards host wing model to be measured；The receiving end of PIV measuring device is installed on support frame
Frame bottom surface, towards host wing model to be measured.
5. being directed to a kind of test method of the dynamical bifurcation generating device of aerodynamic stalling described in claim 1, it is characterised in that:
It is completed by following step:
Step 1: using suitable angle of attack adjustment spring, and adjust adjuster, realize the initial angle of attack tune of wing model to be measured
Section；By the initial angle of attack of angular displacement sensor real-time measurement host wing model to be measured, until host wing model to be measured is initially attacked
Angle reaches measurement request angle；
Step 2: by using suitable sink-float adjustment spring, the sink-float rigidity for adjusting host wing model to be measured has reached requirement just
Degree；
Step 3: adjusting the transmitting end position of PIV measuring device, make it towards the host wing section for needing to measure flow field characteristic；Together
When adjust linear acceleration transducer measurement direction towards host wing model to be measured rise and fall direction；
Step 4: wind-tunnel booting, incoming flow passes through aerofoil, to steady air current；
Step 5: the dirty field characteristic of current air velocity being measured by PIV measuring device, host wing surface is measured by pressure sensor
Dynamic pressure characteristic, by angular displacement sensor measurement host wing rotated around vertical direction angular displacement, by linear acceleration transducer
Host wing is measured along the displacement of the lines characteristic of track of sliding track, is stored in signal monitoring processing system；
Step 6: increasing wind speed, repeat step 5, when wind speed reaches dynamical bifurcation speed, aerofoil starts angle of attack oscillation.
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| CN108182328A (en) * | 2018-01-05 | 2018-06-19 | 北京航空航天大学 | A kind of big angle of attack Nonlinear Aerodynamic reduced-order model suitable for stall flutter |
| CN110348080A (en) * | 2019-06-26 | 2019-10-18 | 南京航空航天大学 | Fighter plane HAOA characteristics analysis method based on Bifurcation Analysis |
| CN111579203A (en) * | 2020-05-29 | 2020-08-25 | 南京航空航天大学 | Two-dimensional airfoil pressure measurement system |
| CN112484951B (en) * | 2020-11-24 | 2022-02-11 | 北京航空航天大学 | Portable wind tunnel test supporting device with adjustable attack angle and two-degree-of-freedom elastic support |
| CN113340557B (en) * | 2021-05-31 | 2022-08-09 | 四川大学 | Water tunnel flow state observation test device for wing suction flow control |
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| US5020364A (en) * | 1990-05-30 | 1991-06-04 | Grumman Aerospace Corporation | Wind tunnel model positioning device |
| CN101419117B (en) * | 2008-11-28 | 2010-06-09 | 北京航空航天大学 | Aeroelastic flutter generating device |
| CN101423115A (en) * | 2008-12-03 | 2009-05-06 | 北京航空航天大学 | Wing with pneumatic reverse effect |
| CN102012308B (en) * | 2010-05-19 | 2012-01-11 | 北京航空航天大学 | Method for jointly and synchronously measuring velocity/pressure during pitching/rolling movement of model |
| CN101986160B (en) * | 2010-05-19 | 2012-11-07 | 北京航空航天大学 | Position-locking shooting method and device for carrying out particle image velocemetry (PIV) measurement under model dynamic pitching |
| US10634580B2 (en) * | 2015-06-04 | 2020-04-28 | The Boeing Company | Systems and methods for analyzing flutter test data using damped sine curve fitting with the closed form shape fit |
| CN105806585A (en) * | 2016-05-11 | 2016-07-27 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel large attack angle pitching dynamic stalling test device |
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