CN206710056U - A kind of aircraft model in wind tunnel erecting device - Google Patents
A kind of aircraft model in wind tunnel erecting device Download PDFInfo
- Publication number
- CN206710056U CN206710056U CN201720351775.2U CN201720351775U CN206710056U CN 206710056 U CN206710056 U CN 206710056U CN 201720351775 U CN201720351775 U CN 201720351775U CN 206710056 U CN206710056 U CN 206710056U
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- CN
- China
- Prior art keywords
- sliding sleeve
- connecting rod
- wind tunnel
- model
- thread segment
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- 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.)
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A kind of aircraft model in wind tunnel erecting device, including fixed guide rail, sliding sleeve is provided with the fixed guide rail, the sliding sleeve side is connected with connecting pole, the connecting pole side is connected with motor, described motor one end is connected with screw rod, thread segment A is provided with the screw rod, thread segment B, the thread segment A, sliding sleeve A is respectively arranged with thread segment B, sliding sleeve B, the sliding sleeve A, sliding sleeve B passes through connecting rod A respectively, connecting rod B connections, the connecting rod A, connecting rod B is connected by fixed plate respectively, several non-slip bumps are provided with the fixed plate surface.Model in wind tunnel erecting device of the present utility model, simple in construction, easy processing, simple installation, it can be achieved to verify for the wind tunnel test with gust load alleviation control system Elastic Aircraft.
Description
Technical field
It the utility model is related to aeroelastic effect test technical field, more particularly to a kind of aircraft model in wind tunnel installation dress
Put.
Background technology
Aircraft, refer to produce the thrust advanced or pulling force by power set, lift is produced by the fixation wing of fuselage, big
The airborne vehicle for overweighting air of flight in gas-bearing formation.It is one kind of Fixed-Wing, and most common one kind, and another kind is solid
It is aerodone to determine wing airborne vehicle.The engine type that aircraft uses according to it can be divided into jet airplane and propeller aeroplane again.
At present in field of aviation measurement and test, aircraft wind tunnel test concentrates on the aerodynamic characteristic of test aircraft body, can not test
The coupled characteristic of control system and aircraft, the coupled characteristic of aircraft rigid motion and structural elasticity vibration can not be tested, for band
The wind tunnel test checking of gust load alleviation control system Elastic Aircraft there is no a kind of effectively practical test device.
Utility model content
The purpose of this utility model is to overcome the technical problem of prior art, there is provided a kind of aircraft model in wind tunnel
Erecting device.
In order to solve the above-mentioned technical problem, the utility model adopts the following technical scheme that：
A kind of aircraft model in wind tunnel erecting device, including guide rail is fixed, sliding sleeve is provided with the fixed guide rail, institute
State sliding sleeve side to be connected with connecting pole, the connecting pole side is connected with motor, and described motor one end connects with screw rod
Connect, thread segment A is provided with the screw rod, is respectively arranged with sliding sleeve A, sliding sleeve on thread segment B, the thread segment A, thread segment B
B, the sliding sleeve A, sliding sleeve B pass through fixation respectively by connecting rod A, connecting rod B connections, the connecting rod A, connecting rod B respectively
Plate is connected, and several non-slip bumps are provided with the fixed plate surface.
As optimal technical scheme of the present utility model, the thread segment A, thread segment B thread rotary orientation are opposite.
As optimal technical scheme of the present utility model, the sliding sleeve A, sliding sleeve B are respectively between connecting rod A, connecting rod B
To be articulated and connected.
As optimal technical scheme of the present utility model, the connecting rod A, connecting rod B connect with fixed plate to be hinged respectively
Connect.
As optimal technical scheme of the present utility model, the non-slip bumps are arc convex shape.
After adopting the above technical scheme, the utility model has the following advantages that：
Model in wind tunnel erecting device of the present utility model, simple in construction, easy processing, simple installation, can be achieved for
Wind tunnel test checking with gust load alleviation control system Elastic Aircraft.
Brief description of the drawings
Specific embodiment of the present utility model is described further below in conjunction with the accompanying drawings：
Fig. 1 is structural representation of the present utility model.
Embodiment
In order that technological means, creation characteristic, reached purpose and effect that the utility model is realized are easy to understand, under
Face with specific embodiments and the drawings, the utility model is expanded on further, but following embodiments are only of the present utility model excellent
Embodiment is selected, and it is not all.Based on the embodiment in embodiment, those skilled in the art are not making creative work
Under the premise of obtain other embodiments, belong to the scope of protection of the utility model.
As shown in figure 1, a kind of aircraft model in wind tunnel erecting device, including guide rail 1 is fixed, on the fixed guide rail 1
Sliding sleeve 2 is provided with, the side of sliding sleeve 2 is connected with connecting pole 3, and the side of connecting pole 3 is connected with motor 4, the drive
Dynamic one end of motor 4 is connected with screw rod 5, thread segment A501, thread segment B502 is provided with the screw rod 5, wherein the thread segment
A501, thread segment B502 thread rotary orientation are opposite.Sliding sleeve A6, cunning are respectively arranged with the thread segment A501, thread segment B502
B7 is covered, wherein the sliding sleeve A6, sliding sleeve B7 are respectively to be articulated and connected between connecting rod A8, connecting rod B9.
As shown in figure 1, the sliding sleeve A6, sliding sleeve B7 pass through connecting rod A8, connecting rod B9 connections, the connecting rod respectively
A8, connecting rod B9 are connected by fixed plate 10 respectively, and several non-slip bumps 11 are provided with the surface of fixed plate 10, wherein
The connecting rod A8, connecting rod B9 are respectively with fixed plate 10 to be articulated and connected, and the non-slip bumps 11 are arc convex shape, this
The model in wind tunnel erecting device of utility model, simple in construction, easy processing, simple installation, it can be achieved for band gust load
Slow down the wind tunnel test checking of control system Elastic Aircraft.So far, the utility model aircraft model in wind tunnel erecting device makes
Described with process.
What deserves to be explained is：In the utility model, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", the term such as " connection ", " fixation " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or
It is integrally connected；Can be mechanically connect, for the ordinary skill in the art, can understand as the case may be on
State concrete meaning of the term in the utility model.
In the utility model, unless otherwise clearly defined and limited, fisrt feature second feature it " on " or it
" under " can directly be contacted including the first and second features, it is not directly to contact but lead to that can also include the first and second features
The other characterisation contact crossed between them.
The advantages of general principle of the present utility model, principal character and the utility model has been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Be only preference of the present utility model, be not intended to limit the utility model, do not departing from the spirit and scope of the utility model
On the premise of, the utility model also has various changes and modifications, and these changes and improvements both fall within this claimed practicality
In new scope.The utility model requires protection scope is by appended claims and its equivalent thereof.
Claims (5)
1. a kind of aircraft model in wind tunnel erecting device, including guide rail (1) is fixed, it is provided with cunning on the fixed guide rail (1)
Cover (2), sliding sleeve (2) side is connected with connecting pole (3), it is characterised in that：Connecting pole (3) side and motor
(4) connect, described motor (4) one end is connected with screw rod (5), and thread segment A (501), screw thread are provided with the screw rod (5)
Section B (502), sliding sleeve A (6), sliding sleeve B (7), the sliding sleeve A are respectively arranged with the thread segment A (501), thread segment B (502)
(6), sliding sleeve B (7) is led to respectively by connecting rod A (8), connecting rod B (9) connection, the connecting rod A (8), connecting rod B (9) respectively
Fixed plate (10) connection is crossed, several non-slip bumps (11) are provided with fixed plate (10) surface.
A kind of 2. aircraft model in wind tunnel erecting device according to claim 1, it is characterised in that：The thread segment A
(501), thread segment B (502) thread rotary orientation is opposite.
A kind of 3. aircraft model in wind tunnel erecting device according to claim 1, it is characterised in that：The sliding sleeve A
(6), sliding sleeve B (7) is respectively to be articulated and connected between connecting rod A (8), connecting rod B (9).
A kind of 4. aircraft model in wind tunnel erecting device according to claim 1, it is characterised in that：The connecting rod A
(8), connecting rod B (9) is respectively to be articulated and connected with fixed plate (10).
A kind of 5. aircraft model in wind tunnel erecting device according to claim 1, it is characterised in that：The non-slip bumps
(11) it is arc convex shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720351775.2U CN206710056U (en) | 2017-04-05 | 2017-04-05 | A kind of aircraft model in wind tunnel erecting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720351775.2U CN206710056U (en) | 2017-04-05 | 2017-04-05 | A kind of aircraft model in wind tunnel erecting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206710056U true CN206710056U (en) | 2017-12-05 |
Family
ID=60467583
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720351775.2U Expired - Fee Related CN206710056U (en) | 2017-04-05 | 2017-04-05 | A kind of aircraft model in wind tunnel erecting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206710056U (en) |
-
2017
- 2017-04-05 CN CN201720351775.2U patent/CN206710056U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171205 Termination date: 20190405 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |