CN201540195U - Freely yawing wind tunnel test device - Google Patents
Freely yawing wind tunnel test device Download PDFInfo
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- CN201540195U CN201540195U CN2009202441338U CN200920244133U CN201540195U CN 201540195 U CN201540195 U CN 201540195U CN 2009202441338 U CN2009202441338 U CN 2009202441338U CN 200920244133 U CN200920244133 U CN 200920244133U CN 201540195 U CN201540195 U CN 201540195U
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Abstract
The utility model relates to a freely yawing wind tunnel test device which can more conveniently and effectively realize the freely yawing wind tunnel test of an aerocraft module. The freely yawing wind tunnel test device comprises the aerocraft module. The utility model is characterized in that the freely yawing wind tunnel test device is also provided with a belly stay supporting rod; the top part of the belly stay supporting rod is fixed with the aerocraft module; and the lower part of the belly stay supporting rod is in a supporting seat, and is provided with a bearing.
Description
Technical field
The utility model relates to a kind of wind tunnel test device of freely going off course.
Background technology
In the wind tunnel test of simulated flight device, need the free yawing rotation of dummy vehicle be detected, in the prior art, lack the wind tunnel test device of freely going off course easy to detect.Simultaneously, need in the wind-tunnel to throw in the flow field trace particle, be used to obtain the characteristic of streaming of air-flow around the dummy vehicle, to analyze the aerodynamic characteristic of dummy vehicle.In the prior art, it all is at the wind-tunnel cup that particle is thrown in, and renders to the left and right sides of the vertical plane of symmetry of model symmetrically because dummy vehicle originally in motion, is difficult to guarantee trace particle, with the characteristic of streaming of real reflection model.
The utility model content
Goal of the invention of the present utility model is to provide a kind of wind tunnel test device of freely going off course, and can realize the wind tunnel test of freely going off course of dummy vehicle more convenient, effectively.
Realize the technical scheme of the present utility model purpose:
A kind of wind tunnel test device of freely going off course comprises dummy vehicle, it is characterized in that: also have belly stay pole, the top and the dummy vehicle of belly stay pole are fixed, and the bottom of belly stay pole is positioned at supporting seat, and bearing is housed.
The bottom of belly stay pole connects rotary encoder through shaft coupling.
The supporting seat bottom is a base, is provided with particle in base, supporting seat, the belly stay pole and throws in passage, and the dummy vehicle both sides of the edge are provided with the slit, and this slit is thrown in passage with particle and is connected.
Also be provided with shoe, shoe connects base through knee, is provided with particle in shoe housing, the knee and throws in passage, and this input passage is thrown in passage with the particle in the base and is connected, and shoe is connected to particle and advances mouth.
The beneficial effect that the utlity model has:
Dummy vehicle of the present utility model and belly stay prop up thick stick and fix, and the belly stay bar is free to rotate, effectively the free yawing rotation of simulated flight device model.Simultaneously, flow out in the slit of particle by the dummy vehicle both sides, can render to more symmetrically in the flow field as trace particle particle is more accurate, can reflect the characteristic of streaming of dummy vehicle better.
Description of drawings
Fig. 1 is the structural representation of the utility model belly stay part;
Fig. 2 is the structural representation of the utility model shoe part.
Embodiment
As shown in Figure 1, the top of belly stay pole 2 and dummy vehicle 1 are fixing, the center of gravity of the corresponding dummy vehicle of point of fixity, and the bottom of belly stay pole is positioned at supporting seat 4, and bearing 3,5 is equipped with in the bottom of belly stay pole.The bottom of belly stay pole 2 connects rotary encoder 7 through shaft coupling 6.The supporting seat bottom is a base 8, is provided with particle in base, supporting seat, the belly stay pole and throws in passage, and the dummy vehicle both sides of the edge are provided with the slit, and this slit is thrown in passage with particle and is connected.
As Fig. 2, shown in Figure 1, also be provided with shoe 10, shoe connects base through knee 9, is provided with particle in shoe housing, the knee and throws in passage, and this input passage is thrown in passage with the particle in the base and is connected, and shoe is connected to particle and advances mouth 11.
Because belly stay pole 2 is free to rotate, during wind tunnel test, dummy vehicle 1 can be realized free yawing rotation under pneumatic power effect, the free crab angle of dummy vehicle 1 can be rotated scrambler 7 records, by the computer acquisition of pulse collection card, can realize that promptly the free yawing rotation time history of dummy vehicle is measured.
The flow field trace particle advances mouth 11 by particle and enters into particle input passage, finally enters in the dummy vehicle, renders in the wind-tunnel by the slit of dummy vehicle both sides of the edge, is used for the FLOW VISUALIZATION of wind tunnel test.Throw in respect to chamber particle before the wind-tunnel of available technology adopting, the wind-tunnel internal particle is thrown in and can be rendered to more symmetrically in the flow field as trace particle particle is more accurate, has cup and throw in incomparable advantage in dynamic test.
Claims (4)
1. the wind tunnel test device of freely going off course comprises dummy vehicle, it is characterized in that: also have belly stay pole, the top and the dummy vehicle of belly stay pole are fixed, and the bottom of belly stay pole is positioned at supporting seat, and bearing is housed.
2. the wind tunnel test device of freely going off course according to claim 1, it is characterized in that: the bottom of belly stay pole connects rotary encoder through shaft coupling.
3. the wind tunnel test device of freely going off course according to claim 1, it is characterized in that: the supporting seat bottom is a base, be provided with particle in base, supporting seat, the belly stay pole and throw in passage, the dummy vehicle both sides of the edge are provided with the slit, and this slit is thrown in passage with particle and is connected.
4. the wind tunnel test device of freely going off course according to claim 3, it is characterized in that: also be provided with shoe, shoe connects base through knee, is provided with particle in shoe housing, the knee and throws in passage, this input passage is thrown in passage with the particle in the base and is connected, and shoe is connected to particle and advances mouth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202441338U CN201540195U (en) | 2009-11-20 | 2009-11-20 | Freely yawing wind tunnel test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202441338U CN201540195U (en) | 2009-11-20 | 2009-11-20 | Freely yawing wind tunnel test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201540195U true CN201540195U (en) | 2010-08-04 |
Family
ID=42591652
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202441338U Expired - Fee Related CN201540195U (en) | 2009-11-20 | 2009-11-20 | Freely yawing wind tunnel test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201540195U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102175419A (en) * | 2010-12-31 | 2011-09-07 | 中国航空工业空气动力研究院 | Large-load abdomen-supporting mechanism |
| CN102818692A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
| CN105258915A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Sideslip angle-varying blade belly supporting device in high-speed wind tunnel test |
| CN105258916A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for correcting influence of high-speed wind tunnel model afterbody distortion on lateral-directional aerodynamic characteristics |
-
2009
- 2009-11-20 CN CN2009202441338U patent/CN201540195U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102175419A (en) * | 2010-12-31 | 2011-09-07 | 中国航空工业空气动力研究院 | Large-load abdomen-supporting mechanism |
| CN102175419B (en) * | 2010-12-31 | 2013-01-23 | 中国航空工业空气动力研究院 | Large-load abdomen-supporting mechanism |
| CN102818692A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
| CN102818692B (en) * | 2012-08-17 | 2015-04-22 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
| CN105258915A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Sideslip angle-varying blade belly supporting device in high-speed wind tunnel test |
| CN105258916A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for correcting influence of high-speed wind tunnel model afterbody distortion on lateral-directional aerodynamic characteristics |
| CN105258916B (en) * | 2015-11-18 | 2017-09-01 | 中国空气动力研究与发展中心高速空气动力研究所 | The modification method that body distortion influences on horizontal course aerodynamic characteristic after a kind of high-speed wind tunnel model |
| CN105258915B (en) * | 2015-11-18 | 2017-09-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Become yaw angle blade belly stay device in a kind of high-speed wind tunnel |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100804 Termination date: 20131120 |