CN106323582B - A kind of device of super-micro size aircraft wind tunnel experiment platform - Google Patents
A kind of device of super-micro size aircraft wind tunnel experiment platform Download PDFInfo
- Publication number
- CN106323582B CN106323582B CN201610778299.2A CN201610778299A CN106323582B CN 106323582 B CN106323582 B CN 106323582B CN 201610778299 A CN201610778299 A CN 201610778299A CN 106323582 B CN106323582 B CN 106323582B
- Authority
- CN
- China
- Prior art keywords
- tacho
- adjustable
- cpu
- experimental section
- frame
- 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.)
- Active
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
- G01M9/02—Wind tunnels
Abstract
The present invention provides a kind of super-micro size aircraft wind tunnel experiment platform device, including integrated flight device experiment frame, experimental section, experimental section support frame, rectification grid, CPU is adjustable tacho, CPU is adjustable tacho fixed frame, guide rail, minute vehicle, in which: integrated flight device experiment frame is in contact with three rectification grids；Integrated flight device experiment frame is in contact with experimental section support frame；Integrated flight device experiment frame is in contact with the adjustable tacho fixed frame of two CPU；Two CPU are adjustable, and tacho fixed frame is in contact with two adjustable tacho of CPU respectively and fixes two adjustable tacho of CPU；Experimental section support frame is in contact with experimental section and fixes experimental section；There is guide rail inside experimental section；Minute vehicle is on guide rail.The present invention realizes the design of the experimental provision to miniature wind-tunnel, realizes the aerodynamic measurement of minute vehicle, realizes the detection of the beating frequency of flivver and the relationship in flow field.
Description
Technical field
The present invention relates to miniature wind tunnel experiment fields, and in particular, to a kind of super-micro size aircraft wind tunnel experiment platform
Device.
Background technique
Wind-tunnel is the very important method of developmental flight device and link.In order to which the flight characteristics and the air that understand aircraft are dynamic
Mechanical characteristic generally requires and carries out a large amount of wind tunnel experiment to aircraft.By aircraft be placed in the flow field of wind tunnel experiment platform into
Row test.Some component of traditional wind tunnel experiment, general multipair aircraft is tested, and subjects are typically all to test mould
Type gets up to be tested by special bracket model support.
Some documents are retrieved, such as Chinese utility model patent 201220024203.0, which is answered
Wire-Driven Parallel Manipulator for aircraft wind tunnel test: " multiple spot is connect with more flexible cables respectively on dummy vehicle, and more
The other end of flexible cable connects electric capstan winch by pulley respectively, and multiple pulleys are separately connected on the stationary platform.The utility model is special
Benefit substitutes traditional bracket using flexible cable traction, so that being reduced to minimum to air velocity distribution influence, and is easier to realize aircraft mould
The variation of type posture makes dummy vehicle wind tunnel test data closer to really " still, it, should as traditional wind tunnel test
The aircraft object of the wind tunnel test of patent is general or test model, the wind tunnel test with true aircraft still have gap
's；In addition although this structure reduces the influence to air velocity distribution, but the flexible cable structure of this complexity be not particularly suited for it is miniature
The wind tunnel test of aircraft, and error also can be bigger, this structure can not solve the flow velocity of air-flow and aircraft wings are clapped
Beat the relations problems between frequency.
Based on this, there is an urgent need to a kind of super-micro size aircraft wind tunnel experiment platform devices, it is made to avoid or reduce above-mentioned shadow
The factor of sound, while extending its application range.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of super-micro size aircraft wind tunnel experiment platforms
Device, described device is using aircraft experiment frame as component, and micrometer fluorescent particle is from described in the warp of the left side of the integration experiment frame
It rectifies grid to enter, then enters experimental section through the adjustable tacho of the CPU and the rectification grid, external high speed camera captures
The dynamic of fluorescent grain, and then observe Flow Field Distribution.
In order to achieve the above object, the present invention provides a kind of device of super-micro size aircraft wind tunnel experiment platform, comprising: one
Change aircraft experiment frame, experimental section, three rectification grids, two adjustable tacho of CPU, guide rail, minute vehicle；Wherein:
The integrated flight device experiment frame be a frame structure, the integrated flight device experiment frame as experimental section,
Three rectification grids, CPU is adjustable tacho, guide rail, minute vehicle carrier；The side of the integrated flight device experiment frame
For a rectangular body cavity；
Three rectification grids, i.e., first rectification grid, second rectification grid, third rectify grid, from left to right according to
Secondary arrangement is in contact with the integrated flight device experiment frame, and is fixed on the integrated flight device experiment frame；
The experimental section is in contact by experimental section support frame with the integrated flight device experiment frame, and is fixed on described
On integrated flight device experiment frame；
Two adjustable tacho of CPU, the i.e. adjustable tacho of the first CPU and the 2nd adjustable tacho of CPU, in which: the
Tacho that one CPU is adjustable is in contact by the adjustable tacho fixed frame of CPU with the integrated flight device experiment frame, and is fixed on
The cuboid of the integrated flight device experiment frame side is intracavitary；The 2nd adjustable tacho of CPU is in contact with third rectification grid,
For going out the air-flow of experimental section by third rectification grid heel row, stablize the flow field of experimental section, while the 2nd CPU can be turned
Fast device is used to effectively prevent the interference of external air flow；
The guide rail is installed on inside the experimental section；
The minute vehicle lies in a horizontal plane on the guide rail and moves along the guide rail.
Preferably, described device is when carrying out wind tunnel test, and micrometer fluorescent particle is from the integrated flight device experiment frame
Side through it is described first rectification grid enter, then through the adjustable tacho of the first CPU and it is described second rectification grid enter
The experimental section；External high speed camera captures the dynamic of fluorescent grain, and then observes Flow Field Distribution, by Flow Field Distribution realization pair
Aerodynamic measurement；
The minute vehicle be placed on the guide rail it is enterprising action mechanics measurement, while detect flow field with it is described miniature
The coupled relation that aircraft is formed；
When the wing of the minute vehicle is not patted, the flow field that the adjustable tacho of the first CPU generates makes
The minute vehicle is obtained to slide along the guide rail；
When the displacement of the minute vehicle does not occur mobile, wind speed and wing pat frequency and form dynamic balance,
To obtain the relationship between the beating frequency of wing and the length and wind speed of wing of the minute vehicle.
Preferably, in the side of experimental section, the third rectifies grid for the first rectification grid and the second rectification grid
In the other side of experimental section, and the second rectification grid and third rectification grid respectively with the two sides phase of the experimental section
Contact.
It is highly preferred that the first rectification grid, the second rectification grid, third rectification grid are by parallel thin plate from level to level
It constitutes；The air-flow that the adjustable tacho of first CPU generates is modulated laminar flow by the second rectification grid, to realize in experimental section
The wind speed of each point in portion is identical, direction is identical, forms steady flow condition.
Preferably, the adjustable tacho of the first CPU can produce the stable air-flow of different wind speed.
Preferably, the integrated flight device experiment frame and the experimental section are transparent, convenient for observation.
Preferably, the minute vehicle is flapping-wing type aircraft；The size of the minute vehicle is in millimeter magnitude.
Preferably, the guide rail is two parallel and smooth filaments, and the friction of guide rail and minute vehicle can ignore that
Disregard, keeps results of wind tunnel more accurate.
Compared with prior art, the invention has the following beneficial effects:
(1) present invention can very well realize the wind tunnel test to minute vehicle.
Integration test is used in the present invention, integrated flight device experiment frame is real as integrated microreactor technology wind-tunnel
Frame is tested, then is linked together with other components, it is simple and compact；Rectification grid is made of parallel thin plate from level to level, will be described
The flow field that tacho that CPU is adjustable is formed is rectified, and makes even flow field and stable entrance experimental section；The guide rail of experimental section is two
The parallel and very smooth filament of item, the friction with minute vehicle can ignore, and keep results of wind tunnel more accurate；It is real
It tests section support frame and experimental section is supported and fixed, keep the position of experimental section firm, and then obtain more accurate wind tunnel test knot
Fruit；Experimental section is transparent, convenient for observation wind tunnel experiment；
(2) compared with other aircraft wind tunnel tests, micrometer fluorescent particle passes through the present invention from the left side of integration experiment frame
The rectification grid enters, then enters experimental section through the adjustable tacho of CPU and rectification grid, and external high speed camera captures fluorescence
The dynamic of particle, and then Flow Field Distribution is observed, there are the advantageous characteristics such as precision is high, error is small, wind tunnel test is convenient, flexible；
(3) present invention realizes the wind tunnel experiment device of micro flapping wing air vehicle, carries out wind tunnel experiment to minute vehicle；
Detect the coupled relation in flow field and minute vehicle formation.When the wing of the minute vehicle is not patted, institute
Stating the flow field that the adjustable tacho of CPU generates slides minute vehicle along guide rail；When the minute vehicle displacement not
When occurring mobile, wind speed and wing pat frequency and form dynamic balance, to obtain the bat of the wing of the minute vehicle
Beat the relationship between frequency and the length and wind speed of wing.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the device overall structure diagrammatic cross-section of a preferred embodiment of the invention,
Fig. 2 is the integrated flight device experiment frame structural schematic diagram of a preferred embodiment of the invention；
Fig. 3 is the rectification grid structural schematic diagram of a preferred embodiment of the invention；
Fig. 4 is the experimental section support frame structure diagram of a preferred embodiment of the invention；
Fig. 5 is the adjustable tacho fixed rack structure schematic diagram of CPU of a preferred embodiment of the invention；
Fig. 6 is the adjustable tacho structural schematic diagram of CPU of a preferred embodiment of the invention；
Fig. 7 is the experimental section structural schematic diagram of a preferred embodiment of the invention；
Fig. 8 is the guide rail structure schematic diagram of a preferred embodiment of the invention；
Fig. 9 is the minute vehicle structural schematic diagram of a preferred embodiment of the invention；
In figure: integrated flight device experiment frame 1 rectifies grid 2,2 ', 2 ", experimental section support frame 3, tacho that CPU is adjustable
Fixed frame 4, tacho that CPU is adjustable 5,5 ', experimental section 6, guide rail 7, minute vehicle 8；
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
As shown in figs. 1-9, a kind of device of super-micro size aircraft wind tunnel experiment platform, comprising: integrated flight device is real
Frame 1 is tested, grid 2,2 ', 2 ", experimental section support frame 3, CPU is adjustable tacho fixed frame 4, tacho that CPU is adjustable 5,5 ', reality are rectified
Test section 6, guide rail 7, minute vehicle 8；Wherein:
The integrated flight device experiment frame 1 is a frame structure, the carrier as other building blocks；
Three the rectification grids 2,2 ', 2 " are in contact and are fixed on integrated with the integrated flight device experiment frame 1
On aircraft experiment frame 1；In the left side of the experimental section, the rectification grid 2 " exists for the rectification grid 2 and rectification grid 2 '
The right side of the experimental section；The rectification grid 2 ' and rectification grid 2 " are in contact with the experimental section；
The experimental section support frame 3 is in contact with the integrated flight device experiment frame 1 and is fixed on integrated flight device
On experiment frame 1；
The adjustable tacho fixed frame 4 of CPU, is in contact with the integrated flight device experiment frame 1 and is fixed on one
Change 1 on aircraft experiment frame；
The adjustable tacho 5 of CPU, is in contact with the adjustable tacho fixed frame 4 of CPU and is fixed on the adjustable tacho of CPU
On fixed frame 4；
The adjustable tacho 5 ' of CPU is in contact with the rectification grid 2 ", described in the air-flow process by the experimental section 6
It is discharged after rectification grid 2 ", stablizes the flow field in the experimental section 6, while the adjustable tacho 5 ' of the CPU can also effectively prevent
The only interference of extraneous air-flow；
The experimental section 6 is in contact with experimental section support frame 3 and is fixed on experimental section support frame 3；
There is the guide rail 7 inside the experimental section 6；The guide rail 7 is two parallel and smooth filaments, with micro air
The friction of device 8 can ignore, and keep results of wind tunnel more accurate.
For the minute vehicle 8 on the guide rail 7, the minute vehicle 8 is flapping-wing type aircraft.
In a preferred embodiment, the rectification grid 2, the rectification grid 2 ', the rectification grid 2 " are by one layer
The parallel thin plate of layer is constituted；The rectification grid 2 ' makes to flow for rectifying the flow field that the adjustable tacho 5 of the CPU is formed
Field is uniform and stable into the experimental section 6.
In a preferred embodiment, the air-flow modulating layer that the rectification grid 2 ' generates the adjustable tacho 5 of the CPU
Stream forms flow field stabilization, it can be achieved that the wind speed of each point the experimental section 6 inside is identical, direction is identical.
In a preferred embodiment, the stable air-flow that the adjustable tacho 5 of the CPU can produce different wind speed passes through described
It rectifies grid 2 ' and enters the experimental section 6；The adjustable steady flow condition for producing friction speed of the adjustable tacho 5 of CPU.
In a preferred embodiment, the integrated flight device experiment frame 1 and the experimental section 6 are transparent, convenient for observation.
In a preferred embodiment, the size of the minute vehicle 8 can be very small, and scale can be in millimeter magnitude.
The course of work of described device is as follows:
Micrometer fluorescent particle enters from the left side of the integrated flight device experiment frame 1 through the rectification grid 2, then through institute
It states the adjustable tacho 5 of CPU and the rectification grid 2 ' enters the experimental section 6, external high speed camera captures fluorescent grain
Dynamically, and then Flow Field Distribution is observed；
By the minute vehicle 8 lie in a horizontal plane in the guide rail 7 it is enterprising action mechanics measurement, while detect flow field with
The coupled relation that the minute vehicle 8 is formed；
When the wing of the minute vehicle 8 is not patted, the flow field that the adjustable tacho 5 of CPU generates makes
Minute vehicle 8 is slided along guide rail 7；
When the displacement of the minute vehicle 8 does not occur mobile, the wing of wind speed and the minute vehicle 8 pats frequency
Rate forms dynamic balance, to obtain the beating frequency of the wing of the minute vehicle 8 and the length and wind speed of wing
Between relationship.
Integration test is used in the present invention, integrated flight device experiment frame is real as integrated microreactor technology wind-tunnel
Frame is tested, then is linked together with other components, it is simple and compact；
Grid is rectified in the present invention to be made of parallel thin plate from level to level, the flow field that the adjustable tacho of the CPU is formed into
Capable rectification makes even flow field and stable entrance experimental section；
The guide rail of experimental section is two parallel and very smooth filaments in the present invention, and the friction with minute vehicle can
It ignores, keeps results of wind tunnel more accurate；
Experimental section is supported and is fixed by experimental section support frame in the present invention, keeps the position of experimental section firm, and then obtain
More accurate results of wind tunnel；
Experimental section is transparent in the present invention, convenient for observation wind tunnel experiment；
Micro-dimension aircraft wind tunnel experiment platform device of the present invention, with precision is high, error is small, wind tunnel test side
Just the advantageous characteristics such as flexible, can be widely used in the wind tunnel experiment of Flapping-wing MAV.
In above-described embodiment attached drawing, identical appended drawing reference represents identical components or acts on same components, and
The similar term such as "upper", "lower" used in description, "front", "rear", "left", "right" only refers to for figure, purpose
It is to easily describe the present invention.
All attached drawings of above-described embodiment, which are intended merely to facilitate, illustrates technology contents of the invention；Constitute optimal implementation
The technical characteristics such as the size of correlation and components between the position of number, components used by mode, components
The restriction to technical solution itself is not constituted, and should extend to the entire field that the technical field is covered.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (7)
1. a kind of super-micro size aircraft wind tunnel experiment platform device characterized by comprising integrated flight device experiment frame, reality
Test section, three rectification grids, two CPU are adjustable tacho, guide rail and minute vehicle；Wherein:
The integrated flight device experiment frame is a frame structure, and the integrated flight device experiment frame is as experimental section, three
Rectify the carrier of grid, CPU is adjustable tacho, guide rail, minute vehicle；The side of the integrated flight device experiment frame is one
Rectangular body cavity；
Three rectification grids, i.e., the first rectification grid, the second rectification grid, third rectify grid, from left to right successively arrange
Column, are in contact with the integrated flight device experiment frame, and be fixed on the integrated flight device experiment frame；
The experimental section is in contact by experimental section support frame with the integrated flight device experiment frame, and is fixed on the one
Change on aircraft experiment frame；
Two adjustable tacho of CPU, the i.e. adjustable tacho of the first CPU and the 2nd adjustable tacho of CPU, in which: the first CPU
Adjustable tacho is in contact by the adjustable tacho fixed frame of CPU with the integrated flight device experiment frame, and is fixed on described
The cuboid of integrated flight device experiment frame side is intracavitary；The 2nd adjustable tacho of CPU is in contact with third rectification grid, is used for
The air-flow of experimental section is gone out by third rectification grid heel row, stablizes the flow field of experimental section, while the 2nd adjustable tacho of CPU
For effectivelying prevent the interference of external air flow；
The guide rail is installed on inside the experimental section；
The minute vehicle lies in a horizontal plane on the guide rail and moves along the guide rail；The guide rail is two parallel and flat
The friction of sliding filament, guide rail and minute vehicle can ignore, and keep results of wind tunnel more accurate；
For described device when carrying out wind tunnel test, micrometer fluorescent particle is from described in the warp of the side of the integrated flight device experiment frame
First rectification grid enters, then enters the experimental section through the adjustable tacho of the first CPU and the second rectification grid；Outside
The dynamic that high speed camera captures fluorescent grain is set, and then observes Flow Field Distribution, is realized by Flow Field Distribution to aerodynamic
Measurement；
The minute vehicle is placed on the measurement of the enterprising action mechanics of the guide rail, while detecting flow field and the micro air
The coupled relation that device is formed；
When the wing of the minute vehicle is not patted, the flow field that the adjustable tacho of the first CPU generates makes institute
Minute vehicle is stated to slide along the guide rail；
When the displacement of the minute vehicle does not occur mobile, wind speed and wing pat frequency and form dynamic balance, thus
Obtain the relationship between the beating frequency of the wing of the minute vehicle and the length and wind speed of wing.
2. a kind of super-micro size aircraft wind tunnel experiment platform device according to claim 1, which is characterized in that described first
Grid and the second rectification grid are rectified in the side of experimental section, the third rectification grid is and described in the other side of experimental section
Second rectification grid and third rectification grid are in contact with the two sides of the experimental section respectively.
3. a kind of super-micro size aircraft wind tunnel experiment platform device according to claim 2, which is characterized in that described first
It rectifies grid, the second rectification grid, third and rectifies grid, be made of multilayer parallel thin plate；The second rectification grid is by the
The air-flow that tacho that one CPU is adjustable generates modulates laminar flow, so that the wind speed of each point of the realization inside experimental section is identical, direction
It is identical, form steady flow condition.
4. a kind of super-micro size aircraft wind tunnel experiment platform device according to claim 1, which is characterized in that described first
Tacho that CPU is adjustable can produce the stable air-flow of different wind speed.
5. a kind of super-micro size aircraft wind tunnel experiment platform device according to claim 1, which is characterized in that the one
Change aircraft experiment frame with the experimental section be it is transparent, convenient for observing.
6. a kind of super-micro size aircraft wind tunnel experiment platform device according to claim 1-5, which is characterized in that
The minute vehicle is flapping-wing type aircraft.
7. a kind of super-micro size aircraft wind tunnel experiment platform device according to claim 6, which is characterized in that described miniature
The size of aircraft is in millimeter magnitude.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610778299.2A CN106323582B (en) | 2016-08-30 | 2016-08-30 | A kind of device of super-micro size aircraft wind tunnel experiment platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610778299.2A CN106323582B (en) | 2016-08-30 | 2016-08-30 | A kind of device of super-micro size aircraft wind tunnel experiment platform |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106323582A CN106323582A (en) | 2017-01-11 |
| CN106323582B true CN106323582B (en) | 2019-09-03 |
Family
ID=57788524
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610778299.2A Active CN106323582B (en) | 2016-08-30 | 2016-08-30 | A kind of device of super-micro size aircraft wind tunnel experiment platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106323582B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112857735A (en) * | 2021-04-02 | 2021-05-28 | 南京工业职业技术大学 | Tug-wheel towing type aircraft mooring experiment table and experiment method thereof |
| CN112857734B (en) * | 2021-04-02 | 2023-03-14 | 南京工业职业技术大学 | Electromagnetic traction type aircraft mooring experiment table and experiment method thereof |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3408719B2 (en) * | 1997-05-30 | 2003-05-19 | 三菱重工業株式会社 | Particle supply device for flowing fluid for fluid visualization and flow measurement |
| US6820477B2 (en) * | 2001-11-14 | 2004-11-23 | Freightliner Llc | Vehicle wind tunnel method and apparatus |
| CN102175420B (en) * | 2011-01-25 | 2013-04-03 | 北京航空航天大学 | Two-degrees-of-freedom supporting system for wind tunnel test of airplane |
| CN103149010B (en) * | 2013-02-22 | 2015-05-06 | 中国人民解放军国防科学技术大学 | NPLS measurement system and method for air inlet channel flow field based on high-supersonic-velocity pulse wind tunnel |
| CN103472256B (en) * | 2013-09-25 | 2015-09-16 | 东南大学 | Based on flowing two-dimension speed field measurement method and the device of area array CCD spatial filter |
| CN103822665B (en) * | 2014-02-28 | 2016-06-29 | 清华大学 | The observation of insect flying form and dynamic property test device |
| CN204807295U (en) * | 2015-06-04 | 2015-11-25 | 傅叶双 | A wind tunnel experiment device for different plate -fin heat exchanger plain fin |
| CN105841913B (en) * | 2016-03-24 | 2019-04-16 | 同济大学 | A kind of wind-tunnel based on intelligent interaction platform |
-
2016
- 2016-08-30 CN CN201610778299.2A patent/CN106323582B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106323582A (en) | 2017-01-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106323582B (en) | A kind of device of super-micro size aircraft wind tunnel experiment platform | |
| CN107228708B (en) | Wing vibration detection device and method based on three-dimensional digital speckle correlation method | |
| CN103471803A (en) | Method for determining aerodynamic parameters of model free flight tests | |
| Sugioka et al. | Unsteady PSP measurement of transonic buffet on a wing | |
| CN107702878A (en) | A kind of flexible fast-response PSP test devices, method and application based on AAO templates | |
| CN208559732U (en) | A kind of high-altitude mapping balloon robot | |
| Ogawa et al. | A field investigation of the flow and diffusion around a model cube | |
| CN103900491B (en) | Device and method for measuring three-core optical fiber space shape based on stimulated Brillouin principle | |
| CN103645339B (en) | A kind of portable wind field wind speed full size height apparatus for measuring distribution | |
| CN204642165U (en) | Miniature self-service mechanomotive force size digital test compound table | |
| CN107762737B (en) | The inspection system and method for wind generator set blade lightning-protection system | |
| CN205719468U (en) | A kind of platform realizing the gentle dynamic test of miniature ornithopter flapping wing Flow visualisation | |
| CN104458192A (en) | Measurement system and measurement method for wind tunnel flow field vortex motion frequency | |
| Pickles et al. | Rotor wake interactions with an obstacle on the ground | |
| Wey et al. | Determination of aerodynamic coefficients from shock tunnel free flight trajectories | |
| Sytsma et al. | Mean loads from wind-tunnel turbulence on low-aspect-ratio flat plates | |
| Fedoul et al. | Experimental study of the aerodynamic characteristics of a low-aspect-ratio flat plate array in a configuration of interest for a tidal energy converter | |
| CN109458937A (en) | Measure method, apparatus, system and the storage medium of grid line height and width | |
| CN110027728A (en) | Pass through the method for the pneumatic focus of airflight test identification aircraft | |
| Babie et al. | An experimental investigation of bending wave instability modes in a generic four-vortex wake | |
| Alhosseinihamedani et al. | Reynolds Number Effect on Lift Characteristics of an Airfoil Translating Across a Non-uniform Approach Flow | |
| Yang et al. | Hysteresis effect on airfoil stall noise and flow field | |
| CN110132525A (en) | Consider the wave of Background wind and the physical simulating method of mobile downburst coupling | |
| CN215810681U (en) | Size detection device is used in production of people's air defense door | |
| CN207816559U (en) | A kind of wind tunnel experiment radome fairing |
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 |