CN206019983U - A kind of aerodynamics of wing experimental simulation device - Google Patents
A kind of aerodynamics of wing experimental simulation device Download PDFInfo
- Publication number
- CN206019983U CN206019983U CN201620762391.5U CN201620762391U CN206019983U CN 206019983 U CN206019983 U CN 206019983U CN 201620762391 U CN201620762391 U CN 201620762391U CN 206019983 U CN206019983 U CN 206019983U
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- wing
- aerodynamics
- blower fan
- simulation device
- model
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Abstract
This utility model is related to a kind of aerodynamics of wing experimental simulation device, the device includes laboratory table, laboratory table is provided with slide rail, blower fan is sequentially provided with slide rail, slidable wire stent and wing model support, blower fan is fixed on one end of slide rail, wire stent upper end is provided with silk thread, wing model pedestal upper end is provided with wing model, silk thread is sailed in the presence of blower fan the surface of wing model, the bottom of laboratory table is additionally provided with the touch screen and driving black box that can be input into experiment parameter, touch screen drives black box to control the distance of the wire stent on slide rail and wing model support and blower fan by connecting control.This utility model provides a kind of clear aerodynamics of wing experimental simulation device directly perceived, easy to operate, being easy to left-hand seat, simple structure, low cost.
Description
Technical field
This utility model is related to a kind of experimental simulation device, fills more particularly, to a kind of aerodynamics of wing experimental simulation
Put.
Background technology
Air stage combustion is a kind of basic means for carrying out aerodynamic studies, studies air by experimental approach
Interaction between the characteristics of motion and air and relative motion object (mainly aircraft).The manufacture and design of aircraft
During, it is requisite to carry out wind tunnel experiment.Large tunnel is typically necessary high expense, in order to reduce expense,
It is reasonable method to take small-sized test experiments in teaching.
Small-sized wind tunnel experiment can only find out the state that air flows in aerofoil surface, test relative to small-sized wind tunnel, in order to
More preferable Data Analysis Services effect is obtained, can be contrasted with experiment using the method for numerical simulation, intuitively speed cloud
Figure, pressure cloud atlas can make learner be apparent from the aerodynamic feature of wing.
Domestic well-known colleges and universities can be built with business tie-up big due to having good stock of knowledge and stronger economic support
The low speed and high-speed wind tunnel of type, can carry out Simulation simultaneously, but so experimental cost can be very high, other ordinary higher learning schools
It is difficult to have same resource.Rarely have in education experiment at present and air stage combustion is directly joined together with analog simulation
Experimental provision, the experimental teaching of colleges and universities lacks the support of necessary experimental facilitiess.
Utility model content
The purpose of this utility model be exactly provide to solve the above problems a kind of easy to operate, be easy to left-hand seat, cost
Low aerodynamics of wing experimental simulation device.
The purpose of this utility model is achieved through the following technical solutions：
A kind of aerodynamics of wing experimental simulation device, the device include that laboratory table, laboratory table are provided with slide rail, slide rail
On be sequentially provided with blower fan, slidable wire stent and wing model support, described blower fan is fixed on one end of slide rail, described
Wire stent upper end be provided with silk thread, described wing model pedestal upper end is provided with wing model, and described silk thread is in blower fan
Sail under effect the surface of wing model,
The bottom of laboratory table is additionally provided with the touch screen and driving black box that can be input into experiment parameter, and described touch screen is by connecting
Connecing control drives black box to control the distance of the wire stent on slide rail and wing model support and blower fan.
Described blower fan outfan be provided with by air-flow rectification for steady air flow commutator.
Described blower fan and commutator are externally provided with protective cover, and the front portion of protective cover is provided with the grid for intersecting anyhow.
The upper end of described wing model support is additionally provided with the rotating mechanism that can change the wing model angle of attack.
Described wire stent and wing model support vertical are on slide rail.
Described drives the controller being provided with black box with touch screen communication.
Described blower fan is mixed flow fan.
The device is additionally provided with the computer for aerodynamics of wing Numerical Simulation in laboratory table, in computer
11 analogue simulation softwares of ANSYS fluent are installed.
The laboratory table bottom of the device is additionally provided with laboratory table support, and the bottom that laboratory table is supported is equipped with universal wheel, universal wheel
It is provided with blocking element.
Compared with prior art, this utility model has advantages below：
1st, this device can be understood by arranging silk thread
Person is acceptant；
2nd, this apparatus structure is simple, and with low cost, laboratory table floor space, it is not necessary to large tunnel, with very strong reality
With property, it is easy to colleges and universities to utilize and popularization and application；
3rd, device intelligence, experiment parameter scalable are compared with existing wing aerodynamic performance demonstration experimental provision, this device
By arranging touch screen and driving black box, different experiment parameters can be set, intelligence degree is high, for abecedarian only needs
A small amount of parameter to be input on the touchscreen, and device just can be with the movement of automatic control model and the adjustment of model angle；
4th, this device is provided with simulation comparison device, after abecedarian tentatively understands aerodynamics of wing characteristic, Ke Yitong
Crossing 11 softwares of ANSYS fluent that installs on computer carries out numerical simulation, and learner can carry out more in-depth study；
5th, the autgmentability of this mounted cast is strong, can install miscellaneous part on aircraft, in order to enter after wing model is dismantled
It is consistent in the threedimensional model that contrast of going can be changed in simulation software simultaneously and experimental facilitiess；
6th, this device has good mobility and stationarity, flexible and convenient operation.This device laboratory table bottom supports dress
It is provided with universal wheel arbitrarily to move, and laboratory table skew after preventing blower fan from starting with blocking element.
Description of the drawings
Fig. 1 is structural representation of the present utility model；
In figure：1- protective covers；2- blower fans；3- commutators；4- grids；5- silk threads；6- wire stents；7- wing models；8-
Rotating mechanism；9- wing model supports；10- computers；11- slide rails；12- laboratory tables are supported；13- drives black box；14- is touched
Screen；15- laboratory tables；16- universal wheels；17- blocking elements.
Specific embodiment
This utility model is described in detail with specific embodiment below in conjunction with the accompanying drawings.
Embodiment 1
A kind of aerodynamics of wing experimental simulation device, its structural representation is as shown in figure 1, the device includes laboratory table
15, slide rail 11 is provided with above laboratory table 15, is provided with blower fan 2, wire stent 6, wing model support 9 on slide rail 11 from front to back,
6 upper end of wire stent is provided with silk thread 5, and 9 upper end of wing model support is provided with wing model 7, is additionally provided with computer in laboratory table 15
10, blower fan 2 is maintained static on slide rail 6, equips commutator 3 on blower fan 2, and the air-flow rectification for producing is steady air flow,
The silk thread 5 in wire stent 6 is blowed to, makes silk thread 5 sail 7 surface of wing model.
Blower fan 2 and commutator 3 are provided with protective cover 1 and grid 4, and protective cover 1 is spindle roll boot, commutator 3
Installed in 2 central rear of blower fan, grid 4 turns in 1 head of protective cover for intersecting anyhow peace, produces can blower fan 2 by rectification
Wind be converted into stable direct current uniform flow field.
This example, blower fan 2 are mixed flow fan, and the mixed flow fan 2 is fixed on the front end of experimental stand 15, mixed-flow wind
Machine model SWF (A) -1 4.5；Flow：3160～4728m3/h；Total head 306～182；Rotating speed：1450r/min；Power/electricity
Pressure：0.55kw/380v；Motor model：Y801-4.
Wire stent 6 is vertical rod, and lower section contacted with slide rail 6, can on slide rail 6 controlled slip, top fixation silk thread
5, the other end of silk thread is freely sagging；9 bottom of wing model support is contacted with slide rail 6, can on slide rail 6 controlled slip, on
Side is rotating mechanism 8, can reach the effect for changing 7 angle of attack of wing model with controlled adjustment angle；Computer 10 is provided with ANSYS
Fluent 11, for carrying out aerodynamics of wing numbered analog simulation, can more be apparent from wing by analog simulation
Aeroperformance.
Drive in black box 13 and Siemens's s7-200plc controllers are housed, for communicating with touch screen 14, touch screen 14 is drive
The display device of the control of dynamic black box 13, by input sliding distance on touchscreen 14 and the parameters such as rotational angle, gives and drives
13 signal of black box, makes driving black box 13 execute order, control wing model support 9 and shifting of the wire stent 6 on slide rail 11
Dynamic and rotating mechanism 8 changes the angle of attack of wing model 7.
In the present embodiment, laboratory table 15 is prepared from using metal material, and geometric parameter is：Height 650mm, length
1600mm, width 600mm.The laboratory table of 15 bottom of laboratory table supports 12 arbitrarily can move equipped with four universal wheels 16, and band
After having blocking element 17 to prevent blower fan 2 from starting, laboratory table 15 offsets.
Rotation dress when pilot demonstration is carried out with analog simulation, by wing model 7 above wing model support 9
Put on 8, switch on power, input sliding distance and the parameters such as rotational angle on touch screen 14 drive the control wire stent 6 of black box 13
The position that touch screen 14 sets is moved on slide rail 11 with wing model support 9, is started blower fan 2, is blowed in wire stent 6
Silk thread 5, make silk thread 5 sail wing model surface.The angle of attack of wing model 7 can be changed on touchscreen 14, according to silk thread 5
On 7 surface of wing model, the state of change can intuitively understand the air dynamic behaviour of wing.While being tested,
11 softwares of ANSYS fluent in computer 10 are opened, is imported in software and identical wing model 7 in experimentation
Threedimensional model file, carries out fluent flow dynamics analysis, obtains pressure, speed cloud atlas through reprocessing analysis, contributes to learning
Habit person understands aerodynamics of wing characteristic in depth.
Claims (9)
1. a kind of aerodynamics of wing experimental simulation device, it is characterised in that the device includes that laboratory table, laboratory table are provided with
Slide rail, is sequentially provided with blower fan, slidable wire stent and wing model support on slide rail, described blower fan is fixed on slide rail
One end, described wire stent upper end are provided with silk thread, and described wing model pedestal upper end is provided with wing model, described silk thread
Sail in the presence of blower fan the surface of wing model,
The bottom of laboratory table is additionally provided with the touch screen and driving black box that can be input into experiment parameter, and described touch screen is controlled by connection
System drives the distance of the wire stent on black box control slide rail and wing model support and blower fan.
2. a kind of aerodynamics of wing experimental simulation device according to claim 1, it is characterised in that described blower fan
Outfan be provided with by air-flow rectification for steady air flow commutator.
3. a kind of aerodynamics of wing experimental simulation device according to claim 2, it is characterised in that described blower fan
Protective cover is externally provided with commutator, the front portion of protective cover is provided with the grid for intersecting anyhow.
4. a kind of aerodynamics of wing experimental simulation device according to claim 1, it is characterised in that described wing
The upper end of model support is additionally provided with the rotating mechanism that can change the wing model angle of attack.
5. a kind of aerodynamics of wing experimental simulation device according to claim 1, it is characterised in that described silk thread
Support and wing model support vertical are on slide rail.
6. a kind of aerodynamics of wing experimental simulation device according to claim 1, it is characterised in that described driving
The controller with touch screen communication is provided with black box.
7. a kind of aerodynamics of wing experimental simulation device according to claim 1, it is characterised in that described blower fan
For mixed flow fan.
8. a kind of aerodynamics of wing experimental simulation device according to claim 1, it is characterised in that the device is in reality
Test the computer being additionally provided with platform for aerodynamics of wing Numerical Simulation.
9. a kind of aerodynamics of wing experimental simulation device according to claim 1, it is characterised in that the reality of the device
Test platform bottom and be additionally provided with laboratory table support, the bottom that laboratory table is supported is equipped with universal wheel, and universal wheel is provided with blocking element.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620762391.5U CN206019983U (en) | 2016-07-19 | 2016-07-19 | A kind of aerodynamics of wing experimental simulation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620762391.5U CN206019983U (en) | 2016-07-19 | 2016-07-19 | A kind of aerodynamics of wing experimental simulation device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206019983U true CN206019983U (en) | 2017-03-15 |
Family
ID=58245301
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620762391.5U Expired - Fee Related CN206019983U (en) | 2016-07-19 | 2016-07-19 | A kind of aerodynamics of wing experimental simulation device |
Country Status (1)
| Country | Link |
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| CN (1) | CN206019983U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107016910A (en) * | 2017-05-20 | 2017-08-04 | 郭茂清 | Multi-functional bernoulli principle Interesting Tests instrument |
| CN109238623A (en) * | 2018-11-13 | 2019-01-18 | 西北工业大学 | A kind of silk thread mounting structure and its installation method for wind tunnel test part |
| CN109357834A (en) * | 2018-11-13 | 2019-02-19 | 西北工业大学 | A kind of fluorescence silk thread mounting structure based on sleeve |
| CN110160738A (en) * | 2019-03-21 | 2019-08-23 | 北京机电工程研究所 | For the fairing of aerofoil wind tunnel test, design method and blended wing-body device |
| CN111915959A (en) * | 2020-08-05 | 2020-11-10 | 中国人民解放军63850部队 | Method and device for simulating RCS (Radar Cross section) of airplane by using RCS of target drone |
| CN114018537A (en) * | 2021-10-21 | 2022-02-08 | 南京航空航天大学 | Wind tunnel internal flow field state detection device and method based on spatial three-dimensional silk thread array |
| CN115959303A (en) * | 2023-03-16 | 2023-04-14 | 四川省天域航通科技有限公司 | Intelligent flight test method and application of large-scale fixed-wing freight unmanned aerial vehicle |
-
2016
- 2016-07-19 CN CN201620762391.5U patent/CN206019983U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107016910A (en) * | 2017-05-20 | 2017-08-04 | 郭茂清 | Multi-functional bernoulli principle Interesting Tests instrument |
| CN109238623A (en) * | 2018-11-13 | 2019-01-18 | 西北工业大学 | A kind of silk thread mounting structure and its installation method for wind tunnel test part |
| CN109357834A (en) * | 2018-11-13 | 2019-02-19 | 西北工业大学 | A kind of fluorescence silk thread mounting structure based on sleeve |
| CN110160738A (en) * | 2019-03-21 | 2019-08-23 | 北京机电工程研究所 | For the fairing of aerofoil wind tunnel test, design method and blended wing-body device |
| CN110160738B (en) * | 2019-03-21 | 2020-10-23 | 北京机电工程研究所 | Rectifying device for wing surface wind tunnel test, design method and wing body fusion device |
| CN111915959A (en) * | 2020-08-05 | 2020-11-10 | 中国人民解放军63850部队 | Method and device for simulating RCS (Radar Cross section) of airplane by using RCS of target drone |
| CN114018537A (en) * | 2021-10-21 | 2022-02-08 | 南京航空航天大学 | Wind tunnel internal flow field state detection device and method based on spatial three-dimensional silk thread array |
| CN115959303A (en) * | 2023-03-16 | 2023-04-14 | 四川省天域航通科技有限公司 | Intelligent flight test method and application of large-scale fixed-wing freight unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170315 Termination date: 20200719 |