CN202886998U - Temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device - Google Patents
Temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device Download PDFInfo
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- CN202886998U CN202886998U CN 201220491217 CN201220491217U CN202886998U CN 202886998 U CN202886998 U CN 202886998U CN 201220491217 CN201220491217 CN 201220491217 CN 201220491217 U CN201220491217 U CN 201220491217U CN 202886998 U CN202886998 U CN 202886998U
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Abstract
The utility model provides a temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device, characterized by comprising a main control computer, a model angle of incidence controller, a redundancy controller, a high precision position adjusting device, a rapid position adjusting device, a positioning mechanism and a position sensor which are mutually coupled and connected. The temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device has the remarkable advantages of not only accurately controlling the angle of incidence of a model, but also automatically controlling a test model to rapidly and accurately return to the zero angle of incidence state through the redundancy controller when the model angle of incidence controller breaks down.
Description
Technical field
The utility model relates to Aero-Space wind tunnel test field, especially relates to a kind of redundancy control apparatus that rushes temporarily the control of formula supersonic wind tunnel angle of attack and design.
Background technology
Angle of attack control device in the wind tunnel test is indispensable for measuring the aerodynamic characteristics of aircraft (or parts) model under the different angles of attack.
Rush temporarily the formula supersonic wind tunnel to start/when cut-offfing, test model is fiercely vibration under the impact of shock load, at this moment, if model is probably understood damage test model and balance not at the zero angle of attack state.
At present, rush temporarily the angle of attack control device of formula supersonic wind tunnel except the servo controller of selecting strong shock resistance, also in topworks, increase in addition manual control loop, when breaking down for servo controller, get back to the zero angle of attack state by artificial manually Control experiment model.This mode needs the artificial fault of finding, then adopts manual mode Control experiment model to get back to the zero angle of attack state, and whole process is consuming time longer, is unfavorable for saving energy consumption, to having relatively high expectations of operator, is difficult to guarantee control accuracy, is prone to misoperation.
Summary of the invention
The purpose of this utility model is: for the problem of prior art existence, provide a kind of and can not only control exactly angle of attack, and can when the angle of attack controller breaks down, get back to quickly and accurately the formula of rushing the temporarily supersonic wind tunnel angle of attack redundancy control apparatus of zero angle of attack state by the automatic Control experiment model of redundant manipulator.
The purpose of this utility model is achieved through the following technical solutions:
A kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily, it is characterized in that, this device comprises main control computer, the angle of attack controller, redundant manipulator, the high precision position conditioning equipment, quick position adjustments equipment, detent mechanism, position transducer, described main control computer respectively with the angle of attack controller, redundant manipulator connects, described angle of attack controller respectively with the high precision position conditioning equipment, quick position adjustments equipment connection, described redundant manipulator respectively with the high precision position conditioning equipment, quick position adjustments equipment connection, described high precision position conditioning equipment, position adjustments equipment all is connected with detent mechanism fast, described detent mechanism is connected with position transducer, this position transducer is connected with redundant manipulator with the angle of attack controller respectively and is connected, and described angle of attack controller is connected with redundant manipulator.
Described main control computer communication is connected with redundant manipulator with the angle of attack controller by the CAN bus respectively.
Described high precision position conditioning equipment is that flow is at the servo-valve of 160L/min ~ 250L/min.
The preferred flow of described high precision position conditioning equipment is the servo-valve of 200L/min.
Described quick position adjustments equipment is that flow is at the servo-valve of 300L/min ~ 400L/min.
The preferred flow of described quick position adjustments equipment is the servo-valve of 350L/min.
Described detent mechanism is servo-cylinder.
Described position transducer is magnetostrictive displacement sensor.
Compared with prior art, the utility model can be when accurately controlling angle of attack, automatic acquisition angle of attack controller failure information, and the Control experiment model is got back to the zero angle of attack state quickly and accurately automatically, has guaranteed the safety of test model and balance.
Description of drawings
Fig. 1 is structural representation of the present utility model.
Embodiment
Below in conjunction with the drawings and specific embodiments the utility model is elaborated.
Embodiment 1
As shown in Figure 1: a kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily, this device comprise main control computer 1, angle of attack controller 2, redundant manipulator 3, high precision position conditioning equipment 4, quick position adjustments equipment 5, detent mechanism 6, position transducer 7.Main control computer 1 is connected with angle of attack controller 2, redundant manipulator 3 by the CAN bus respectively.Angle of attack controller 2 is connected with high precision position conditioning equipment 4, quick position adjustments equipment 5 respectively.Redundant manipulator 3 is connected with high precision position conditioning equipment 4, quick position adjustments equipment 5 respectively.High precision position conditioning equipment 4, quick position adjustments equipment 5 all are connected with detent mechanism 6.Detent mechanism 6 is connected with position transducer 7, and this position transducer 7 is connected with angle of attack controller 2 respectively is connected connection with redundant manipulator.Angle of attack controller 2 is connected with redundant manipulator 3.
Wherein, main control computer is the PXI real-time controller; Angle of attack controller and redundant manipulator are HNC100 numeral axis controller; The high precision position regulating device is high frequency sound servo-valve (200L/min); Apparatus for adjusting position is that large-flow high-frequency rings servo-valve (350L/min) fast; Detent mechanism is servo-cylinder, and position transducer is magnetostrictive displacement sensor.
The course of work is: when wind tunnel test was carried out, main control computer 1 was simultaneously to angle of attack controller 2, redundant manipulator 3 sending controling instructions; Angle of attack controller 2 is controlled the accurate location that the high precision position conditioning equipment is realized detent mechanism 6 according to the feedback information of the position transducer 7 that is connected with detent mechanism 6; During off-test, angle of attack controller 2 control high precision position conditioning equipments 4 and quick position adjustments equipment 5 make model get back to fast the zero angle of attack state.
In the process of the test, the running status of redundant manipulator 3 real time monitoring angle of attack controllers 2, if capture failure message, then take over the control of angle of attack controller 3, automatically control high precision position conditioning equipment 4 and quick position adjustments equipment 5 make model get back to quickly and accurately the zero angle of attack state.
Embodiment 2
A kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily, its high precision position regulating device is high frequency sound servo-valve (160L/min), its quick apparatus for adjusting position is that large-flow high-frequency rings servo-valve (300L/min).The remaining part of control device is identical with embodiment 1.
A kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily, its high precision position regulating device is high frequency sound servo-valve (250L/min), its quick apparatus for adjusting position is that large-flow high-frequency rings servo-valve (350L/min).The remaining part of control device is identical with embodiment 1.
The above only is preferred embodiment of the present utility model; not in order to limit the utility model; should be pointed out that all any modifications of within spirit of the present utility model and principle, doing, be equal to replacement and improvement etc., all should be included within the protection domain of the present utility model.
Claims (8)
1. one kind is rushed formula supersonic wind tunnel angle of attack redundancy control apparatus temporarily, it is characterized in that, this device comprises main control computer, the angle of attack controller, redundant manipulator, the high precision position conditioning equipment, quick position adjustments equipment, detent mechanism, position transducer, described main control computer respectively with the angle of attack controller, redundant manipulator connects, described angle of attack controller respectively with the high precision position conditioning equipment, quick position adjustments equipment connection, described redundant manipulator respectively with the high precision position conditioning equipment, quick position adjustments equipment connection, described high precision position conditioning equipment, position adjustments equipment all is connected with detent mechanism fast, described detent mechanism is connected with position transducer, this position transducer is connected with redundant manipulator with the angle of attack controller respectively and is connected, and described angle of attack controller is connected with redundant manipulator.
2. a kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily according to claim 1 is characterized in that, described main control computer communication is connected with redundant manipulator with the angle of attack controller by the CAN bus respectively.
3. a kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily according to claim 1 is characterized in that, described high precision position conditioning equipment is that flow is at the servo-valve of 160L/min ~ 250L/min.
4. a kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily according to claim 3 is characterized in that, the preferred flow of described high precision position conditioning equipment is the servo-valve of 200L/min.
5. a kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily according to claim 1 is characterized in that, described quick position adjustments equipment is that flow is at the servo-valve of 300L/min ~ 400L/min.
6. a kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily according to claim 3 is characterized in that, the preferred flow of described quick position adjustments equipment is the servo-valve of 350L/min.
7. a kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily according to claim 1 is characterized in that, described detent mechanism is servo-cylinder.
8. a kind of formula supersonic wind tunnel angle of attack redundancy control apparatus that rushes temporarily according to claim 1 is characterized in that, described position transducer is magnetostrictive displacement sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220491217 CN202886998U (en) | 2012-09-25 | 2012-09-25 | Temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220491217 CN202886998U (en) | 2012-09-25 | 2012-09-25 | Temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device |
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| Publication Number | Publication Date |
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| CN202886998U true CN202886998U (en) | 2013-04-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201220491217 Expired - Fee Related CN202886998U (en) | 2012-09-25 | 2012-09-25 | Temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108572054A (en) * | 2017-03-13 | 2018-09-25 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of intermittent wind tunnel simulation experiment method and device |
| CN109269758A (en) * | 2018-10-30 | 2019-01-25 | 北京航天益森风洞工程技术有限公司 | A kind of wind-tunnel Three Degree Of Freedom model interposer control system and method |
| CN110471461A (en) * | 2019-08-28 | 2019-11-19 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of wind tunnel model angle of attack control device and its control method |
| CN112082727A (en) * | 2020-09-08 | 2020-12-15 | 中国航空工业集团公司哈尔滨空气动力研究所 | Control device applied to translational oscillation test of model with automatic variable attack angle |
-
2012
- 2012-09-25 CN CN 201220491217 patent/CN202886998U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108572054A (en) * | 2017-03-13 | 2018-09-25 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of intermittent wind tunnel simulation experiment method and device |
| CN109269758A (en) * | 2018-10-30 | 2019-01-25 | 北京航天益森风洞工程技术有限公司 | A kind of wind-tunnel Three Degree Of Freedom model interposer control system and method |
| CN110471461A (en) * | 2019-08-28 | 2019-11-19 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of wind tunnel model angle of attack control device and its control method |
| CN112082727A (en) * | 2020-09-08 | 2020-12-15 | 中国航空工业集团公司哈尔滨空气动力研究所 | Control device applied to translational oscillation test of model with automatic variable attack angle |
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| Date | Code | Title | Description |
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| 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: 20130417 Termination date: 20150925 |
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| EXPY | Termination of patent right or utility model |