CN203365102U - An ejection-type large-attack-angle mechanism used for a wind-tunnel - Google Patents
An ejection-type large-attack-angle mechanism used for a wind-tunnel Download PDFInfo
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- CN203365102U CN203365102U CN 201320433167 CN201320433167U CN203365102U CN 203365102 U CN203365102 U CN 203365102U CN 201320433167 CN201320433167 CN 201320433167 CN 201320433167 U CN201320433167 U CN 201320433167U CN 203365102 U CN203365102 U CN 203365102U
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Abstract
An ejection-type large-attack-angle mechanism used for a wind-tunnel is used for presetting a 20-degree angle before a wind-tunnel test. The wind-tunnel-used ejection-type large-attack-angle mechanism comprises a model support pole seat, a head-bent support pole, a power apparatus, and a tail cone. The support pole seat, the power apparatus, and bend pole are all mutually connected through hinges. The ejection-type large-attack-angle mechanism is installed on an external wind tunnel support. The tail cone is in threaded connection with an end of the support pole, and the head-bent pole is fixed on the wind-tunnel support. According to the wind-tunnel-used ejection-type large-attack-angle mechanism of the utility model, under a condition that a wind tunnel is not subjected to large-scale machinery reconstruction, the maximum attack-angle can be increased for 20 degrees when a model is in a test. On one hand, a requirement for the large-attack-angle test of an aerospace aviation aircraft is satisfied, and on the other hand, high costs needed for carrying out machinery reconstruction on the wind tunnel are saved. The wind-tunnel-used ejection-type large-attack-angle mechanism is simple in structure, convenient and fast to operate, and high in efficiency.
Description
Technical field
The utility model relates to the large attack angle mechanism of ejection type for a kind of wind-tunnel, belongs to the wind tunnel test technical field.
Background technology
The fast development of Aero-Space cause, for the high maneuverability of realizing weapon can need to carry out large angles-of-attack.So the ground wind tunnel test has also been proposed to large angle of attack requirement.At present, Asia is-15 °～15 ° across super wind-tunnel attack angle mechanism variation range, can first preset 5 ° of angles of attack before test, and it is 20 ° that attack angle mechanism can produce the maximum angle of attack, still far can not meet aircraft and carry out high angle-of-attack testing.If realize large angle of attack function by changing whole construction of wind tunnel, technical difficulty is large, and the funds cost is high, the transformation cycle is long.For meeting the requirement of aerospace flight vehicle to large angle of attack wind tunnel test, the structure of wind-tunnel is not carried out to large change again simultaneously, need to propose a kind of large attack angle mechanism, meet the high angle-of-attack testing of aerospace flight vehicle.
The utility model content
Technology of the present utility model deal with problems for: overcome the deficiencies in the prior art, for meeting the requirement of aerospace flight vehicle to large angle of attack wind tunnel test, the structure of wind-tunnel is not carried out to large change again simultaneously, a kind of large attack angle mechanism of pneumatic ejection type that can realize preset 20 ° of angles of attack has been proposed, have simple in structure, reliability is high, the advantage such as convenient to operation.
Technical solution of the present utility model is:
The large attack angle mechanism of ejection type for a kind of wind-tunnel, for preset 20 ° of angles of attack before wind tunnel test, comprising: model pole pedestal, elbow pole, propulsion system and tail cone;
Together with described model pole pedestal, propulsion system and elbow pole all are connected through the hinge between any two, by on the large attack angle mechanism of described ejection type wind-tunnel support mounted externally, tail bone is connected with the end thread of elbow pole, and elbow pole is fixed on described air leg.
Described model pole pedestal comprises taper hole, the first keyway, tension wedge groove and anti-cleat slot; Described model pole pedestal is connected with outer struts by taper hole, and the first keyway matches with the key on described outer struts, the rolling degree of freedom of restriction outer struts, and tension wedge groove and anti-cleat slot are respectively used to described outer struts tension and reject.
Described elbow pole comprises spacing inclined-plane, taper pin-hole and the second keyway; The mating surface of described elbow pole and model pole pedestal is spacing inclined-plane, and the position of spacing inclined-plane restriction model pole pedestal, by taper pin-hole, makes the axis of described taper hole be parallel to the axis of tail cone; Described the second keyway matches with the key on outside wind-tunnel support, by the rolling degree of freedom of the second keyway restriction elbow pole.
Described propulsion system comprise cylinder and airflow pipeline, and cylinder promotes the model pole pedestal pole rotation of going for a stroll, and making angle between the axis of the axis of taper hole and tail cone is 20 °, and airflow pipeline and high pressure gas holder are connected, and will be filled with gases at high pressure in cylinder.
The utility model has the advantages that:
In the situation that wind-tunnel is not carried out to large machine rebuilding, can make the model maximum angle of attack at the trial increase by 20 °.Having met aerospace flight vehicle carries out the requirement of test at high attack angle on the one hand, has saved on the other hand wind-tunnel is carried out to the needed high cost of machine rebuilding.Whole apparatus structure is simple, convenient to operation, efficient.
The accompanying drawing explanation
Fig. 1 is the utility model structural representation
Embodiment
The utility model proposes a kind of large attack angle mechanism of pneumatic ejection type that can realize preset 20 ° of angles of attack, this apparatus structure is simple, reliability is high, convenient to operation, can not realize large angle of attack function in the situation that wind-tunnel is not carried out to large the change simultaneously.Can meet the high angle-of-attack testing of aerospace flight vehicle.
As shown in Figure 1, the large attack angle mechanism of the utility model ejection type comprises: the model pole pedestal 100 coordinated with the pole tail end, elbow pole 200, propulsion system 300 and a tail cone 400.Model pole pedestal 100, elbow pole 200 and propulsion system 300 all are connected through the hinge between any two, form four-bar mechanism, and the rear end of elbow pole 200 is installed on the wind-tunnel support, and is strained and fixed with tail bone 400.
Elbow pole 200 comprises spacing inclined-plane 201, taper pin-hole 202 and the second keyway 203; The mating surface of described elbow pole 200 and model pole pedestal 100 is spacing inclined-plane 201, and the position of spacing inclined-plane 201 restriction model pole pedestals 100, by taper pin-hole 202, makes the axis of described taper hole 101 be parallel to the axis of tail cone 400; Described the second keyway 203 matches with the key on outside wind-tunnel support, by the rolling degree of freedom of the second keyway 203 restriction elbow poles 200.
When carrying out test at high attack angle, whole large attack angle mechanism is assembled into to integral body in the manner described above, as shown in the figure.Then the cylinder mating surface of the elbow pole 200 at keyway 203 places is inserted on the support in wind-tunnel.Open air circuit breaker and be filled with gases at high pressure by airflow pipeline 302 to cylinder 301, cylinder 301 promotion model pole pedestals 100 are the confined planes 201 to elbow pole 200 around hinge axis.Due to the axis of tail cone 400 and the angle of 201 one-tenth 20 ° of elbow pole confined planes, so realized the function of the preset 20 ° of angles of attack of model pole.The outer struts that test model is housed is inserted in the taper hole 101 of model pole pedestal 100, and by tension wedge groove 103, model pole is tightened on the model pole pedestal to 100 with the chock piece.Thereby realized original angle of attack scope has been increased to 20 °.
Claims (4)
1. the large attack angle mechanism of ejection type for wind-tunnel, for preset 20 ° of angles of attack before wind tunnel test, is characterized in that comprising: model pole pedestal (100), elbow pole (200), propulsion system (300) and tail cone (400);
Described model pole pedestal (100), propulsion system (300) and elbow pole (200) all are connected through the hinge together between any two, by on the large attack angle mechanism of described ejection type wind-tunnel support mounted externally, tail bone (400) is connected with the end thread of elbow pole (200), and elbow pole (200) is fixed on described air leg.
2. according to claim 1 a kind of pneumatic with the large attack angle mechanism of ejection type, it is characterized in that: described model pole pedestal (100) comprises taper hole (101), the first keyway (102), tension wedge groove (103) and anti-cleat slot (104);
Described model pole pedestal (100) is connected with outer struts by taper hole (101), the first keyway (102) matches with the key on described outer struts, the rolling degree of freedom of restriction outer struts, tension wedge groove (103) and anti-cleat slot (104) are respectively used to described outer struts tension and reject.
3. according to claim 1 a kind of pneumatic with the large attack angle mechanism of ejection type, it is characterized in that: described elbow pole (200) comprises spacing inclined-plane (201), taper pin-hole (202) and the second keyway (203); The mating surface of described elbow pole (200) and model pole pedestal (100) is spacing inclined-plane (201), and spacing inclined-plane (201) limit the position of model pole pedestal (100), by taper pin-hole (202), make the axis of described taper hole (101) be parallel to the axis of tail cone (400); Described the second keyway (203) matches with the key on outside wind-tunnel support, by the rolling degree of freedom of the second keyway (203) restriction elbow pole (200).
4. according to claim 1 a kind of pneumatic with the large attack angle mechanism of ejection type, it is characterized in that: described propulsion system (300) comprise cylinder (301) and airflow pipeline (302), cylinder (301) promotes model pole pedestal (a 100) pole (200) rotation of going for a stroll, making angle between the axis of the axis of taper hole (101) and tail cone (400) is 20 degree, airflow pipeline (302) is connected with high pressure gas holder, will be filled with gases at high pressure in cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320433167 CN203365102U (en) | 2013-07-18 | 2013-07-18 | An ejection-type large-attack-angle mechanism used for a wind-tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320433167 CN203365102U (en) | 2013-07-18 | 2013-07-18 | An ejection-type large-attack-angle mechanism used for a wind-tunnel |
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| CN203365102U true CN203365102U (en) | 2013-12-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201320433167 Expired - Fee Related CN203365102U (en) | 2013-07-18 | 2013-07-18 | An ejection-type large-attack-angle mechanism used for a wind-tunnel |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840583A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of big attack angle mechanism of sub- transonic and supersonic wind tunnel with translation functions |
| CN107290123A (en) * | 2017-06-07 | 2017-10-24 | 中国航天空气动力技术研究院 | The big angle of attack device of multiple degrees of freedom wind-tunnel |
| CN109506877A (en) * | 2018-12-11 | 2019-03-22 | 中国航天空气动力技术研究院 | It is a kind of sub- across 90 ° of the super wind-tunnel big angle of attack, 360 ° of rolling devices of coupling |
| CN116399546A (en) * | 2023-06-07 | 2023-07-07 | 中国航空工业集团公司沈阳空气动力研究所 | Low-blocking-degree large-attack-angle driving mechanism and driving method for aircraft model |
-
2013
- 2013-07-18 CN CN 201320433167 patent/CN203365102U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840583A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of big attack angle mechanism of sub- transonic and supersonic wind tunnel with translation functions |
| CN106840583B (en) * | 2016-12-29 | 2019-12-20 | 中国航天空气动力技术研究院 | Sub-span supersonic wind tunnel large attack angle mechanism with translation function |
| CN107290123A (en) * | 2017-06-07 | 2017-10-24 | 中国航天空气动力技术研究院 | The big angle of attack device of multiple degrees of freedom wind-tunnel |
| CN107290123B (en) * | 2017-06-07 | 2019-05-24 | 中国航天空气动力技术研究院 | The big angle of attack device of multiple degrees of freedom wind-tunnel |
| CN109506877A (en) * | 2018-12-11 | 2019-03-22 | 中国航天空气动力技术研究院 | It is a kind of sub- across 90 ° of the super wind-tunnel big angle of attack, 360 ° of rolling devices of coupling |
| CN116399546A (en) * | 2023-06-07 | 2023-07-07 | 中国航空工业集团公司沈阳空气动力研究所 | Low-blocking-degree large-attack-angle driving mechanism and driving method for aircraft model |
| CN116399546B (en) * | 2023-06-07 | 2023-09-12 | 中国航空工业集团公司沈阳空气动力研究所 | Low-blocking-degree large-attack-angle driving mechanism and driving method for aircraft model |
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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 |
Granted publication date: 20131225 Termination date: 20160718 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |