CN206192620U - A model strutting arrangement for multimachine formation wind tunnel test - Google Patents
A model strutting arrangement for multimachine formation wind tunnel test Download PDFInfo
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- CN206192620U CN206192620U CN201621311221.1U CN201621311221U CN206192620U CN 206192620 U CN206192620 U CN 206192620U CN 201621311221 U CN201621311221 U CN 201621311221U CN 206192620 U CN206192620 U CN 206192620U
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Abstract
The utility model provides a model strutting arrangement for multimachine formation wind tunnel test, belongs to the experimental technique of wind tunnel field, the utility model discloses a solve the form into columns support problem of in experimental a plurality of models of multimachine. The utility model discloses a structural style is that back of the body branch is fixed at main tributary pole left end, and the ring joint nestification is on the main tributary pole, and board -like bracing piece is installed in the ring joint, but that the translation connects is nested on board -like bracing piece, but rotatable taper sleeve passes through gland nut fixes on the translation connects, and balance branch is installed on rotatable taper sleeve. The utility model discloses a model strutting arrangement for multimachine formation wind tunnel test can support the tanker aircraft model simultaneously and receive oily quick -witted model to the realization receives oily quick -witted model to put the change for the space support position of tanker aircraft model.
Description
Technical field
The utility model is related to a kind of model supporting device, and in particular to a kind of model for multiple aircraft formation wind tunnel test
Support meanss, belong to wind tunnel technique field.
Background technology
It is aerial plus, be related to that multiple aircraft formation, refuelling platform be overall, pneumatic, structure collaborative design is, it is necessary to break through by oil tech
The design concept of the single platform of tradition, i.e., in wind tunnel experiment, the support meanss in its wind-tunnel can only support a model aircraft
Tested；By cooperative system design, realize air refuelling safely, be rapidly completed air refueling mission.At present in the world
Only the flourishing country of some aeronautical technologies carried out formation wind- tunnel investigation, once carried out large-scale fuel charger to one in wind-tunnel
Frame large aircraft refuels to form into columns and tests, and the technology belongs to blank stage at home.Accordingly, it would be desirable to one kind can simultaneously support many
The wind tunnel test support meanss of individual model aircraft, so as to meet the model support demand of multiple aircraft formation wind tunnel test.
Utility model content
The purpose of this utility model is to provide a kind of model supporting device for multiple aircraft formation wind tunnel test, many to solve
The support of multiple models, the problem of locus conversion in machine formation experiment.
A kind of model supporting device for multiple aircraft formation wind tunnel test include the back of the body pole, main strut, ring joint,
Board-like support bar, translatable joint, clamp nut, rotatable tapered sleeve and balance pole；
Back of the body pole is fixed on main strut left end, and ring joint is nested on main strut, and board-like support bar connects installed in annular
On head, translatable joint is nested on board-like support bar, and rotatable tapered sleeve is fixed on translatable joint by clamp nut, day
Flat pole is arranged on rotatable tapered sleeve.
Preferably：Balance pole is provided with the conical surface being engaged with rotatable tapered sleeve.
Preferably：Ring joint can horizontally slip on main strut, and can be rotated around main strut；Translatable joint can
Slided up and down on board-like support bar, and fixed by jackscrew.
Preferably：Back of the body pole is connected with board-like support bar with main strut and ring joint by screw and pin.
Preferably：Back of the body pole lower end is connected with fuel charger model, and balance pole left end is connected with refueled aircraft model.
Preferably：Translatable joint, clamp nut and rotatable tapered sleeve composition leveling structure.
The utility model has the following effects that compared with existing product：Can realize supporting two in a supporting construction
Or multiple models, it is ensured that formation model is tested under the conditions of same Flow Field in Wind Tunnel；Back of the body pole and board-like support bar section are equal
Be aerofoil profile or thin board type structure, with rigidity it is high, disturb small the characteristics of；Can realize appointing between balance pole and translatable joint
The anglec of rotation of meaning, the support of refueled aircraft model uses the moveable polar coordinates structure type of origin, can conveniently realize any
Put by oil level in space.
Brief description of the drawings
Fig. 1 is a kind of front view of model supporting device for multiple aircraft formation wind tunnel test described in the utility model；
Fig. 2 is the side view of Fig. 1；
Fig. 3 is schematic diagram of the refueled aircraft model below fuel charger model starboard wing；
Fig. 4 is leveling structure sectional view.
In figure：1- back ofs the body pole, 2- main struts, 3- ring joints, the board-like support bars of 4-, the translatable joints of 5-, 6- compress spiral shell
Mother, the rotatable tapered sleeves of 7-, 8- balances pole, 9- fuel chargers model, 10- refueled aircraft models.
Specific embodiment
The utility model is elaborated below according to accompanying drawing preferred embodiment.
As shown in Figures 1 to 4, a kind of model supporting device for multiple aircraft formation wind tunnel test described in the utility model
Including back of the body pole 1, main strut 2, ring joint 3, board-like support bar 4, translatable joint 5, clamp nut 6, the and of rotatable tapered sleeve 7
Balance pole 8；
The back of the body pole 1 is fixed on the left end of main strut 2, and ring joint 3 is nested on main strut 2, and board-like support bar 4 is installed
In ring joint 3, translatable joint 5 is nested on board-like support bar 4, and rotatable tapered sleeve 7 is fixed on by clamp nut 6 can
In translation joint 5, balance pole 8 is arranged on rotatable tapered sleeve 7, and back of the body pole 1 lower end is connected with fuel charger model 9, balance branch
The left end of bar 8 is connected with refueled aircraft model 10, and ring joint 3 can horizontally slip on main strut 2, and can be revolved around main strut 2
Turn；Translatable joint 5 can be slided up and down on board-like support bar 4, and be fixed by jackscrew, translatable joint 5, clamp nut
6 and the composition leveling structure of rotatable tapered sleeve 7, main strut 2, ring joint 3, board-like support bar 4 and translatable joint 5 constitute one
The translatable polar form motion of origin, refueled aircraft model 10 can be supported to any locus in stroke,
By changing the board-like support bar 4 with different pre- inclination angles, it is possible to achieve refueled aircraft model 10 is different relative to fuel charger model 9
The change of the angle of attack, rotatable tapered sleeve 7 is adjusted by clamp nut 6, can be in any locus by the attitude of refueled aircraft model 10
Leveling.
Further：Balance pole 8 is provided with the conical surface being engaged with rotatable tapered sleeve 7.
Further：Back of the body pole 1 is fixed with board-like support bar 4 with main strut 2 and ring joint 3 by screw and pin.
Present embodiment is the exemplary illustration to this patent, does not limit its protection domain, people in the art
Member can also be changed to its part, as long as no the Spirit Essence beyond this patent, all in the protection domain of this patent.
Claims (6)
1. a kind of model supporting device for multiple aircraft formation wind tunnel test, it is characterised in that：Including back of the body pole (1), main strut
(2), ring joint (3), board-like support bar (4), translatable joint (5), clamp nut (6), rotatable tapered sleeve (7) and balance branch
Bar (8)；
Back of the body pole (1) is fixed on main strut (2) left end, and ring joint (3) is nested on main strut (2), board-like support bar
(4) in ring joint (3), translatable joint (5) is nested on board-like support bar (4), and rotatable tapered sleeve (7) is by pressure
Tight nut (6) is fixed on translatable joint (5), and balance pole (8) is on rotatable tapered sleeve (7).
2. a kind of model supporting device for multiple aircraft formation wind tunnel test according to claim 1, it is characterised in that：My god
Flat pole (8) is provided with the conical surface being engaged with rotatable tapered sleeve (7).
3. a kind of model supporting device for multiple aircraft formation wind tunnel test according to claim 1, it is characterised in that：Ring
Shape joint (3) can horizontally slip on main strut (2), and can be rotated around main strut (2)；Translatable joint (5) can be in plate
Formula support bar is slided up and down on (4), and is fixed by jackscrew.
4. a kind of model supporting device for multiple aircraft formation wind tunnel test according to claim 1 or 3, its feature exists
In：Back of the body pole (1) is fixed with board-like support bar (4) with main strut (2) and ring joint (3) by screw and pin.
5. a kind of model supporting device for multiple aircraft formation wind tunnel test according to claim 1 and 2, its feature exists
In：Back of the body pole (1) lower end is connected with fuel charger model (9), and balance pole (8) left end is connected with refueled aircraft model (10).
6. a kind of model support for multiple aircraft formation wind tunnel test according to any claim in claims 1 to 3
Device, it is characterised in that：Translatable joint (5), clamp nut (6) and rotatable tapered sleeve (7) composition leveling structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621311221.1U CN206192620U (en) | 2016-12-02 | 2016-12-02 | A model strutting arrangement for multimachine formation wind tunnel test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621311221.1U CN206192620U (en) | 2016-12-02 | 2016-12-02 | A model strutting arrangement for multimachine formation wind tunnel test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206192620U true CN206192620U (en) | 2017-05-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621311221.1U Active CN206192620U (en) | 2016-12-02 | 2016-12-02 | A model strutting arrangement for multimachine formation wind tunnel test |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768800A (en) * | 2016-12-02 | 2017-05-31 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of model supporting device for multiple aircraft formation wind tunnel test |
| CN108106809A (en) * | 2017-12-14 | 2018-06-01 | 大连四达高技术发展有限公司 | Low blockage percentage support device |
| CN112880963A (en) * | 2021-01-18 | 2021-06-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Double-machine supporting device for double-machine oiling wind tunnel test |
-
2016
- 2016-12-02 CN CN201621311221.1U patent/CN206192620U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768800A (en) * | 2016-12-02 | 2017-05-31 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of model supporting device for multiple aircraft formation wind tunnel test |
| CN108106809A (en) * | 2017-12-14 | 2018-06-01 | 大连四达高技术发展有限公司 | Low blockage percentage support device |
| CN112880963A (en) * | 2021-01-18 | 2021-06-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Double-machine supporting device for double-machine oiling wind tunnel test |
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