CN107525647A - A kind of dynamical bifurcation generating means of aerodynamic stalling - Google Patents
A kind of dynamical bifurcation generating means of aerodynamic stalling Download PDFInfo
- Publication number
- CN107525647A CN107525647A CN201710619568.5A CN201710619568A CN107525647A CN 107525647 A CN107525647 A CN 107525647A CN 201710619568 A CN201710619568 A CN 201710619568A CN 107525647 A CN107525647 A CN 107525647A
- Authority
- CN
- China
- Prior art keywords
- measured
- main frame
- angle
- wing
- bifurcation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- 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
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention discloses a kind of dynamical bifurcation generating means of aerodynamic stalling, sets exhibition to be connected to main frame wing model to be measured vertically, its taper rotating shaft by angular displacement sensor with support frame top surface sliding block in support frame；Root rotating shaft is connected with support frame bottom surface slipper bearing；Make main frame wing model to be measured that there is fore-and-aft 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 governor motion adjusts main frame wing model sink-float rigidity to be measured；Be also equipped with host wing to be measured the angular displacement sensor of the angle that the measurement host wing rotates around vertical direction, measurement host wing surface dynamic pressure numerical value pressure sensor；The PIV measurement apparatus of measurement flow field characteristic is installed in support frame.The checking to dynamical bifurcation Numerical Simulation Results caused by aerodynamic stalling is can be achieved in the present invention, and provides amendment for theoretical modeling, and the strategy of practicable increase dynamical bifurcation speed is proposed with this.
Description
Technical field
It is that a kind of dynamical bifurcation of aerodynamic stalling fills the invention belongs to aviation aircraft design and wind energy conversion system field
Put, specifically one kind is directed to Fixed Wing AirVehicle wing, rotor craft rotor, pneumatic equipment bladess and occurs pneumatically to lose
The experimental system of its dynamic response and dynamical bifurcation is measured after speed.
Background technology
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 subtracts
Small, air-flow adheres to again, lift increase, so repeatedly, the pitching generation self-sustained oscillation on structure pitch freedom.It is this by
Stall flutter is also commonly referred to as in dynamical bifurcation caused by aerodynamic stalling, is a kind of serious aeroelasticity wild effect.Greatly
Aspect ratio wing, especially solar powered aircraft are larger because wing tip deforms, and wing tip can be made to be in a very big angle of attack, easily
Aerodynamic stalling is brought it about, and then triggers dynamical bifurcation, serious destruction will be caused to body when serious.Other helicopter rotation
Dynamical bifurcation situation can also occur for the wing and propeller.The propeller rotated, when the angle of attack increases to stall zone, it will go out
The dynamical bifurcation of existing aerodynamic stalling.It is not dependent on the feature of the classical flutter such as inertia force, elastic force and aerodynamic force
Condition, its key are because aerodynamic force issues angry dynamics stall in big situations of attack and caused, therefore are a kind of more complicated non-
Linear dynamics phenomenon.
Generally, when the angle of attack reaches the scope of stall, the characteristics of can showing is that aerodynamic force starts in aerofoil surface
Separate, after separation reaches to a certain degree, lift caused by aerodynamic force drastically declines, and acts on returning on wing
Multiple power will make the wing angle of attack diminish, and air-flow is attached to aerofoil surface again because the angle of attack diminishes, and recovers the lift of wing, such as
This is reciprocal, and in pitch orientation vertical dip mining occurs for wing.Aerodynamic stalling is occurring, wing enters after vertical dip mining state, no
Same speed of incoming flow, the amplitude of vertical dip mining are different.It is often the case that vertical dip mining occurs suddenly under a certain speed for wing,
And do not restrain, increase when with speed of incoming flow, a variety of changes, referred to as dynamical bifurcation phenomenon can be presented in vertical dip mining amplitude, this
Caused by the phenomenon mainly aerodynamic force as caused by aerodynamic force stall is non-linear.
The mechanism of dynamical bifurcation caused by research aerodynamic force stall at present also mainly based on numerical simulation, but due to
Force measurements and the process of stall be sufficiently complex, uncertainty, the aircaft configuration parameter that unsteady aerodynamic force simulation is assumed
Uncertainty, numerical simulation are needed by verification experimental verification.Invention dynamical bifurcation generating means is needed, can be with quantitative study aerodynamic force
The condition and influence factor that dynamical bifurcation caused by stall occurs, and after diverging wing structure response condition,
Reliable experimental condition is provided, so as to find out the effective means for suppressing or improving dynamical bifurcation speed by laboratory facilities.
Problems with is primarily present in simulation of the wind-tunnel realization to wing stall flutter：
1. dynamical bifurcation characteristic and the initial angle of attack of wing and equilbrium position there are much relations, how to design and adjustable initially attack
Angle and balance position mechanism and its measuring mechanism.
2. the main reason for as dynamical bifurcation, unsteady aerodynamic force dynamic characteristic measuring is more multiple during aerodynamic force stall
Miscellaneous, its stall event is difficult to occur, and the dynamic variation characteristic of aerodynamic force is not easy to catch.
Based on the above situation, it is necessary to propose a kind of dynamical bifurcation phenomenon that can accurately produce wing aerodynamic power stall
Experimental rig and method, to provide reference for correlative study.
The content of the invention
In view of the above-mentioned problems, the present invention proposes a kind of dynamical bifurcation device of aerodynamic stalling, its application is to be directed to
There may be the aircraft of aerodynamic stalling dynamical bifurcation phenomenon, gyroplane and wind energy conversion system, it can produce and be caused by aerodynamic force stall
Dynamical bifurcation phenomenon, and unsteady aerodynamic force dynamic characteristic and wing dynamic response are measured, for exploratory flight device
Or pneumatic equipment bladess dynamical bifurcation characteristic.
The dynamical bifurcation generating means of aerodynamic stalling of the present invention, main frame wing model to be measured is set inside support frame, treated
Survey main frame wing model to open up to vertically, taper rotating shaft is connected by angular displacement sensor with the sliding block of support frame top surface.
Root rotating shaft is connected by bearing with the sliding block of support frame bottom surface；Make main frame wing model to be measured with shifting along the longitudinal direction
The dynamic free degree, and the rotational freedom around vertical direction.The angle of attack of host wing to be measured is adjusted by angle of attack governor motion, is treated
The sink-float rigidity for surveying main frame wing model is adjusted by sink-float governor motion.
Angular displacement, the measurement host wing surface rotated for the measurement host wing around vertical direction is also equipped with host wing to be measured
Dynamic pressure numerical value pressure sensor.PIV measurement apparatus for measuring flow field characteristic is installed in support frame simultaneously.
When being tested, the initial angle of attack of main frame wing model to be measured is adjusted by bringing up governor motion, and adjust to be measured
The sink-float rigidity of main frame wing model, which reaches, requires rigidity.Then increase wind speed and stably in a value, measure under the flow velocity
The dynamic response characteristic of flow field characteristic, aerofoil surface Pneumatic pressure characteristic and wing, pass through phenomenon and structure, pneumatic gauging number
It is judged that dynamic stall characteristic and dynamical bifurcation characteristic；And by changing wind speed, measure the dynamical bifurcation characteristic under different wind speed.
The advantage of the invention is that：
1st, the dynamical bifurcation generating means of aerodynamic stalling of the present invention, the dynamical bifurcation as caused by aerodynamic stalling is faced on ground
Simulated, the checking to dynamical bifurcation Numerical Simulation Results caused by aerodynamic stalling can be achieved, and provide and repair for theoretical modeling
Just, the strategy of practicable increase dynamical bifurcation speed is proposed with this, there is important practical value.
2nd, in the dynamical bifurcation generating means of aerodynamic stalling of the present invention, for controlling the bullet of wing pitching and the rigidity that rises and falls
Spring group and initial angle adjusting means can be changed, and be easy to set the different initial angles of attack and different torsions and sink-float
Rigidity, for studying the factor for influenceing aerodynamic force stall and dynamical bifurcation spot speed.
3rd, the dynamical bifurcation generating means of aerodynamic stalling of the present invention, favorable repeatability, workable, cost is relatively low
It is honest and clean, and installation operation is simple, application easy to spread, the dynamical bifurcation for being highly suitable for producing under aerodynamic force stall condition shows
As, and measure critical data.
4th, the dynamical bifurcation generating means of aerodynamic stalling of the present invention, it can be used for binary wing panel, wing, high aspect ratio and fly
The dynamical bifurcation characteristic research of the aerodynamic force stall of each class formations such as row device wing, large fan.
Brief description of the drawings
Fig. 1 is the dynamical bifurcation generating means overall structure diagram of aerodynamic stalling of the present invention.
In figure：
1- support frame 2- sliding equipment 3- angle of attack governor motions
4- sink-float governor motion 5- linear acceleration transducer 6- angular displacement sensors
7- pressure sensor 8-PIV measurement apparatus 9- signal monitoring processing systems
10- main frame wing model 11- pressure taps 201- crossbeams to be measured
202- slide rail 203- sliding block 301- swing arms
The 302- angles of attack adjust spring 303- adjusters
Embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
The dynamical bifurcation generating means of aerodynamic stalling of the present invention, including support frame 1, sliding equipment 2, angle of attack regulation machine
Structure 3, rise and fall governor motion 4, linear acceleration transducer 5, angular displacement sensor 6, pressure sensor 7, PIV measurement apparatus 8 and letter
Number monitoring processing system 9, as shown in Figure 1.
Support of the support frame 1 as dynamical bifurcation generating means of the present invention, it is cube structure.Support frame 1
Top surface and the mounting surface that bottom surface is sliding equipment 2, are provided with a set of sliding equipment 2 in an identical manner respectively.As shown in figure 1,
Sliding equipment 2 includes two crossbeams 201 set along the left and right directions of support frame 1, and one sets along the fore-and-aft direction of support frame 1
The slide rail 202 put；Slide rail 202 is installed between two crossbeams 201, and slide rail 202 is centrally located at the end face center of support frame 1；
Sliding block 203 is slidably fitted with the slide rail 202.
Main frame wing model 10 to be measured, main frame to be measured are installed between sliding equipment 2 on the above-mentioned top surface of support frame 1 and bottom surface
The covering that wing model 10 is laid by main frame wing skeleton with main frame wing skeleton outer wall is formed.Main frame wing model 10 to be measured is opened up to along perpendicular
Nogata is at the center of support frame 1.The taper rotating shaft of main frame wing model 10 to be measured is fixed on by angular displacement sensor 6
On sliding block in the top surface sliding equipment 2 of support frame 1；Root rotating shaft is directly mounted at the bottom surface of support frame 1 by bearing and slided
On sliding block in mechanism 2.Thus, main frame wing model 10 to be measured is made with one-movement-freedom-degree along the longitudinal direction, and around vertical
The rotational freedom in direction；Changed with time by the angle of attack of 6 measurable host wing of angular displacement sensor.Host wing to be measured
Linear acceleration transducer 5 is also pasted in the taper rotating shaft of model, for measurement host wing sink-float acceleration.
The angle of attack governor motion 3 has two sets, respectively on a cross section of the top of support frame 1 and bottom.
Two sets of angle of attack governor motions 3 are formed by 301, four angle of attack regulation springs 302 of swing arm with two adjusters 303.Wherein, position
In the angle of attack governor motion 3 on the top of support frame 1：The taper that the center of swing arm 301 is fixedly sheathed in main frame wing model to be measured turns
On axle.It is respectively angle of attack regulation spring A, B, C, D to make four angle of attack regulation springs 302；Two adjusters 303 use gaily decorated basket spiral shell
Silk, respectively adjuster A and B；Spring A is adjusted on front side of the left end of swing arm 301 by the angle of attack with the front side of support frame 1 to be connected, swing arm
Spring B is adjusted on rear side of 301 left ends by the angle of attack with adjuster A to be connected, adjuster A is connected with the rear side of support frame 1；And the angle of attack
Regulation spring A, angle of attack regulation spring B and adjuster A are coaxial, and axis is located on the left surface of support frame 1.The right-hand member of swing arm 301
Front side adjusts spring C by the angle of attack and is connected with adjuster B, and adjuster B is connected with the front side of support frame 1；After the right-hand member of swing arm 301
Side is connected by spring D with the rear side of support frame 1；Same angle of attack regulation spring C, angle of attack regulation spring D and adjuster B are coaxial,
Axis is located on the right flank of support frame 1.Angle of attack governor motion 3 positioned at the bottom of support frame 1 is with being located in support frame 1
The mounting means of the angle of attack governor motion 3 in portion is identical.In above-mentioned angle of attack governor motion 3, angle of attack regulation spring 302 is used to provide
The rigidity of the wing model angle of attack direction free degree to be measured is controlled, by being adjusted in synchronism four adjusters 303, makes four adjusters
303 elongations are identical, and then equal length stretching angle of attack regulation spring, realize the angle of attack regulation of main frame wing model to be measured.
The sink-float governor motion 4 is two sets, is respectively arranged in the top of support frame 1 and bottom；Rise and fall governor motion 4
Formed for two sink-float regulation springs 401；Wherein, in the sink-float governor motion 4 on the top of support frame 1, two sink-float regulation bullets
Spring 401 is located at the taper rotating shaft offside of main frame wing model 10 to be measured, one end and the taper rotating shaft phase of main frame wing model 10 to be measured respectively
Even, the other end is connected with side before and after support frame 1 respectively；And two sink-float regulation springs 401 are coaxial, axis is located at carriage
On the place cross section of 1 top angle of attack governor motion of frame 3.The sink-float governor motion 4 of the bottom of support frame 1 and the top of support frame 1
The mounting means of sink-float governor motion 4 it is identical, and the axis of sink-float governor motion 4 of the bottom of support frame 1 is located under support frame
On the place cross section of portion's angle of attack governor motion 3.Thus, the sink-float rigidity of two sets of sink-float adjustable main wings of governor motion 4 is passed through
Characteristic.
The pressure sensor 7 is installed on main frame wing model to be measured using the dynamic pressure transducer of unsteady aerodynamic force
Inside 10, and positioned at the middle part of main frame wing model 10 to be measured.Simultaneously pressure tap is provided with the middle part wall of main frame wing model 10 to be measured
11, for installing pressure-measuring pipe, pressure-measuring pipe one end connection pressure sensor 10, the other end outside main frame wing model 10 to be measured with connecting
It is logical；Pass through the dynamic pressure numerical value of the measurable main frame wing surface of pressure sensor 7, real-time display aerodynamic stalling characteristic.
The transmitting terminal of the PIV measurement apparatus 8 is installed on the left side wall of support frame 1, towards main frame wing model to be measured
10, laser can be launched in left-right direction.The receiving terminal of PIV measurement apparatus 8 is installed on the bottom surface of support frame 1, towards main frame to be measured
Wing model 10, receive the formation image vertically returned.
Above-mentioned linear acceleration transducer 5, pressure sensor 6, angular displacement sensor 7, the receiving terminal of PIV measurement apparatus 8 are equal
It is connected with signal monitoring processing system 9, measurement signal can be sent to signal monitoring processing system 9 and be handled.
When being tested by the dynamical bifurcation generating means of aerodynamic stalling of the present invention, as shown in figure 1, specific steps are such as
Under：
Step 1：Spring 302, and regulation adjuster are adjusted by using the suitable angle of attack, is realized to spring rate system
Number and the regulation of tensile elongation, and then realize the initial angle of attack regulation of wing model 10 to be measured；Angle displacement transducer in said process
Device 8 measures the initial angle of attack of main frame wing model 10 to be measured in real time, until the initial angle of attack of main frame wing model 10 to be measured reaches measurement
Required angle.
Step 2：Spring 401 is adjusted by using suitable sink-float, the sink-float rigidity for adjusting main frame wing model 10 to be measured arrives
Reach requirement rigidity.
Step 3：The transmitting end position of PIV measurement apparatus 8 is adjusted, makes it towards the host wing for needing measurement flow field characteristic
Section.The measurement direction of linear acceleration transducer 5 is adjusted simultaneously to rise and fall direction towards main frame wing model to be measured.
Step 4：Wind-tunnel is started shooting, and incoming passes through aerofoil, treats steady air current.
Step 5：The dirty field characteristic of current air velocity is measured by PIV measurement apparatus 8, by the measurement host of pressure sensor 6
Wing surface dynamic pressure characteristic, the angular displacement rotated by the measurement host wing of angular displacement sensor 7 around vertical direction, accelerated by line
Displacement of the lines characteristic of the measurement host wing of sensor 5 along the track of slide rail 202 is spent, is stored in signal monitoring processing system 9, is observed
Experimental phenomena.
Step 6：Increase wind speed, repeat step 5 is tested, and when wind speed reaches dynamical bifurcation speed, aerofoil starts pitching and shaken
Swing；
By above-mentioned steps 1~6, judge dynamic stall characteristic eventually through phenomenon and structure, pneumatic gauging data and move
Dynamical bifurcation characteristic under state Bifurcation Characteristics, and the different wind speed of measurement.
After one group of experiment is completed, return to step 1, wing model to be measured is adjusted to the new initial angle of attack, is carried out different
Dynamical bifurcation experiment under state.
Claims (7)
- A kind of 1. dynamical bifurcation generating means of aerodynamic stalling, it is characterised in that：Host wing to be measured is set inside support frame Model, main frame wing model to be measured are opened up to vertically, and taper rotating shaft passes through the cunning of angular displacement sensor and support frame top surface Block is connected；Root rotating shaft is connected by bearing with the sliding block of support frame bottom surface；Main frame wing model to be measured is set to have 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 is adjusted by angle of attack governor motion Section, the sink-float rigidity of main frame wing model to be measured are adjusted by sink-float governor motion；The angular displacement that is also equipped with rotating around vertical direction for the measurement host wing on host wing to be measured, measurement host wing surface The pressure sensor of dynamic pressure numerical value；PIV measurement apparatus for measuring flow field characteristic is installed in support frame simultaneously.
- A kind of 2. dynamical bifurcation generating means of aerodynamic stalling as claimed in claim 1, it is characterised in that：Angle of attack governor motion position In top and lower position in support frame；Angle of attack governor motion has the swing rod being installed in main frame wing model rotating shaft to be measured, And swing rod both ends are provided with coaxial two springs and an adjuster；Two springs are located at swing rod offside, one end with pendulum Bar connects, and the other end connects support frame and adjuster respectively, and adjuster is connected with support frame；The regulation at swing rod both ends simultaneously Device is located at swing rod offside.By being adjusted in synchronism top and the adjuster in the angle of attack governor motion of lower section, spring elongation length is realized Synchronous adjustment, and then realize the regulation of host wing Model angle of attack to be measured.
- A kind of 3. dynamical bifurcation generating means of aerodynamic stalling as claimed in claim 2, it is characterised in that：Top and lower section are attacked Angle governor motion is respectively above support frame and on two cross sections of lower section.
- A kind of 4. dynamical bifurcation generating means of aerodynamic stalling as claimed in claim 1, it is characterised in that：Sink-float governor motion be Two sets, support frame top and bottom are respectively arranged in, is made up of two coaxial sink-float regulation springs；Two sink-float regulation bullets Spring is located at main frame wing model rotating shaft offside to be measured, and one end is connected with main frame wing model rotating shaft to be measured, the other end respectively with carriage Frame is connected.
- A kind of 5. dynamical bifurcation generating means of aerodynamic stalling as claimed in claim 1, it is characterised in that：Pressure sensor is installed In in main frame wing model to be measured, and in the middle part of main frame wing model to be measured；It is provided with simultaneously on main frame wing model middle wall face to be measured Pressure tap, installation pressure-measuring pipe in pressure tap, pressure-measuring pipe one end connection pressure sensor, the other end with outside main frame wing model to be measured Connection.
- A kind of 6. dynamical bifurcation generating means of aerodynamic stalling as claimed in claim 1, it is characterised in that：PIV measurement apparatus Transmitting terminal is installed in support frame side wall, towards main frame wing model to be measured；The receiving terminal of PIV measurement apparatus is installed on carriage Frame bottom surface, towards main frame wing model to be measured.
- 7. a kind of dynamical bifurcation generating means of aerodynamic stalling described in application claim 1 is tested, it is characterised in that：It is logical Cross following step completion：Step 1：Spring, and regulation adjuster are adjusted using the suitable angle of attack, realize that the initial angle of attack of wing model to be measured is adjusted Section；The initial angle of attack of main frame wing model to be measured is measured in real time by angular displacement sensor, until the initial of main frame wing model to be measured is attacked Angle reaches measurement request angle；Step 2：Spring is adjusted by using suitable sink-float, the sink-float rigidity for adjusting main frame wing model to be measured has reached requirement just Degree；Step 3：The transmitting end position of PIV measurement apparatus is adjusted, makes it towards the main frame wing section for needing measurement flow field characteristic；Together When adjust linear acceleration transducer measurement direction towards main frame wing model to be measured rise and fall direction；Step 4：Wind-tunnel is started shooting, and incoming passes through aerofoil, treats steady air current；Step 5：The dirty field characteristic of current air velocity is measured by PIV measurement apparatus, by pressure sensor measurement host wing surface Dynamic pressure characteristic, the angular displacement rotated by the angular displacement sensor measurement host wing around vertical direction, by linear acceleration transducer Displacement of the lines characteristic of the measurement host wing along track of sliding track, is stored in signal monitoring processing system；Step 6：Increase wind speed, repeat step 5, when wind speed reaches dynamical bifurcation speed, aerofoil starts angle of attack vibration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710619568.5A CN107525647B (en) | 2017-07-26 | 2017-07-26 | A kind of dynamical bifurcation generating device of aerodynamic stalling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710619568.5A CN107525647B (en) | 2017-07-26 | 2017-07-26 | A kind of dynamical bifurcation generating device of aerodynamic stalling |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107525647A true CN107525647A (en) | 2017-12-29 |
| CN107525647B CN107525647B (en) | 2019-06-25 |
Family
ID=60680035
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710619568.5A Active CN107525647B (en) | 2017-07-26 | 2017-07-26 | A kind of dynamical bifurcation generating device of aerodynamic stalling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107525647B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112484951A (en) * | 2020-11-24 | 2021-03-12 | 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 |
| CN113340557A (en) * | 2021-05-31 | 2021-09-03 | 四川大学 | Water tunnel flow state observation test device for wing suction flow control |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5020364A (en) * | 1990-05-30 | 1991-06-04 | Grumman Aerospace Corporation | Wind tunnel model positioning device |
| CN101419117A (en) * | 2008-11-28 | 2009-04-29 | 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 |
| CN101986160A (en) * | 2010-05-19 | 2011-03-16 | 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 |
| CN102012308A (en) * | 2010-05-19 | 2011-04-13 | 北京航空航天大学 | Method and device for jointly and synchronously measuring velocity/pressure during pitching/rolling movement of model |
| 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 |
| CN106240839A (en) * | 2015-06-04 | 2016-12-21 | 波音公司 | For analyzing the system and method for flutter test data |
-
2017
- 2017-07-26 CN CN201710619568.5A patent/CN107525647B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5020364A (en) * | 1990-05-30 | 1991-06-04 | Grumman Aerospace Corporation | Wind tunnel model positioning device |
| CN101419117A (en) * | 2008-11-28 | 2009-04-29 | 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 |
| CN101986160A (en) * | 2010-05-19 | 2011-03-16 | 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 |
| CN102012308A (en) * | 2010-05-19 | 2011-04-13 | 北京航空航天大学 | Method and device for jointly and synchronously measuring velocity/pressure during pitching/rolling movement of model |
| CN106240839A (en) * | 2015-06-04 | 2016-12-21 | 波音公司 | For analyzing the system and method for flutter test data |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 赵德敏: ""非线性颤振系统的分岔与混沌"", 《中国博士学位论文全文数据库 工程科技II辑》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112484951A (en) * | 2020-11-24 | 2021-03-12 | 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 |
| 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 |
| CN113340557A (en) * | 2021-05-31 | 2021-09-03 | 四川大学 | Water tunnel flow state observation test device for wing suction flow control |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107525647B (en) | 2019-06-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107525647A (en) | A kind of dynamical bifurcation generating means of aerodynamic stalling | |
| US5627311A (en) | Transportable three-dimensional calibration wind tunnel system, verification method of flight control system and flight simulator using same | |
| CN108132134A (en) | Aerodynamic derivative discrimination method and system based on wind tunnel free flight test | |
| CN109297666A (en) | A kind of stage separation flow tunnel testing device and test method based on two sets of movement mechanisms | |
| CN109977448A (en) | A kind of rotor aerodynamics analysis method based on actual measurement structural loads | |
| CN108427322A (en) | A kind of modeling method of the big flexible flier based on on-line identification | |
| CN114577433B (en) | Wind tunnel virtual flight test balance aerodynamic force acquisition and processing system | |
| CN102494864A (en) | Device for simulating free yawing/rolling movement under pitching movement of aircraft | |
| CN116086756B (en) | Ground simulation test method for balancing helicopter whole machine in forward flight state | |
| CN114216649B (en) | Hypersonic separation flow control test device and method | |
| Gonzalez-Rocha et al. | Measuring atmospheric winds from quadrotor motion | |
| Metzger et al. | Measuring the 3-D wind vector with a weight-shift microlight aircraft | |
| CN104503258B (en) | Coaxial double-rotary wing depopulated helicopter modeling method based on fiber cable laying | |
| CN109823566A (en) | A kind of vertically taking off and landing flyer flight control system test platform | |
| Kennell et al. | Free flight testing in hypersonic flows: HEXAFLY-INT EFTV | |
| CN104391364B (en) | Coaxial double-rotary wing depopulated helicopter parameter identification pilot system based on fiber cable laying | |
| CN106774385A (en) | A kind of dirigible spot hover control method of use adaptive variable structure | |
| CN113204196A (en) | Rocket boosting launching simulation method for small and medium-sized unmanned aerial vehicles | |
| Lundström et al. | Testing of atmospheric turbulence effects on the performance of micro air vehicles | |
| CN114910244A (en) | Full-aircraft model gust load alleviation wind tunnel test method based on forward-looking feedback | |
| Namirian et al. | Modeling and Wind Flow Analysis of an Eiffel (Open) Type Sub-Sonic Wind Tunnel | |
| Loeser et al. | Development of the dynamic wind tunnel testing capabilities at DNW-NWB | |
| Oehler | Measuring apparent flow vector on a flexible wing kite | |
| Subke | Test installations to investigate the dynamic behaviour of aircraft with scaled models in wind tunnels | |
| CN115290282B (en) | Wind tunnel test method for researching course control efficiency of control surface of flying wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |