CN203083804U - Experiment device realizing thrust deflexion - Google Patents
Experiment device realizing thrust deflexion Download PDFInfo
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- CN203083804U CN203083804U CN 201220689525 CN201220689525U CN203083804U CN 203083804 U CN203083804 U CN 203083804U CN 201220689525 CN201220689525 CN 201220689525 CN 201220689525 U CN201220689525 U CN 201220689525U CN 203083804 U CN203083804 U CN 203083804U
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- air feed
- pipeline
- pressure measurement
- jet flow
- jet
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Abstract
An experiment device realizing thrust deflexion comprises an experiment model, a main force balance, a jet flow airforce measuring balance, a total pressure measuring segment, a static pressure measuring segment, a jet flow system, high pressure air feed flexible pipes, pneumatic pressure-regulating valves and an air feed support arm. The experiment model is connected with the air feed support arm and are then placed in a wind tunnel. The main force balance, the jet flow airforce measuring balance, the total pressure measuring segment and the static pressure measuring segment are arranged in sequence in the experiment model. The jet flow system comprises a secondary flow air feed pipeline and a main jet flow pipeline respectively arranged in the experiment model, is connected with a high pressure air source pipeline through the two high pressure air feed flexible pipes and the pneumatic pressure-regulating valves, and the high pressure air source pipeline is respectively connected with the total pressure measuring segment, the static pressure measuring segment, a final exhaust nozzle and a static pressure hole of the static pressure measuring segment through the main jet flow pipeline and the secondary flow air feed pipeline. The experiment device realizing thrust deflexion is simple in structure and easy in mounting and dismounting, and can simultaneously and accurately control and measure flow parameters of the secondary flow and the main jet flow.
Description
Technical field
The utility model relates to aviation aerodynamic force experimental technique field, particularly relates to the high-speed wind tunnel Pneumatic method and realizes the thrust deflexion experimental provision.
Background technology
The thrust deflexion technology is to improve the maneuverability of modern combat aircraft, agility at present, improves the pneumatic-propulsion system integrated technique of In-Flight Performance, also is one of extensive advanced technology that adopts of New-Generation Fighter.Practice shows, it is broken through the stall barrier in modern combat aircraft, realizes big angle of attack post stall maneuver, strengthens susceptibility and maneuverability, improve fight capability, reduce the landing distance that takes off, improve the aircraft takeoffs and landings characteristic and improve aspect such as the stealthy characteristic of aircraft having a very important role.High-speed wind tunnel Pneumatic method realization thrust deflexion experimental facilities can be realized the active Flow Control of jet flow, thereby changes the jet deflexion direction, realizes thrust deflexion, satisfies the design object of following aircraft high maneuverability, high agility and high stealth.
The utility model content
The technical problems to be solved in the utility model is, provide a kind of simple for structure, the parameter of main element obtains through pneumatic design or calculating, installation, convenient disassembly, simultaneously can accurately control and measure the flow parameter of secondary flow and main jet stream, be applicable to the wind tunnel experiment device of the employing Pneumatic method realization thrust deflexion of various models.
The technical scheme that adopts is:
A kind of experimental provision of realizing thrust deflexion comprises test model, main force balance, jet flow aerodynamic force measurement balance, total pressure measurement section, static pressure measurement section, jet flow system, high-pressure air feed flexible pipe, air vent valve door, air feed support arm.Described test model connects the air feed support arm, and is arranged in the wind-tunnel.Be laid with the main force balance of measurement model aerodynamic force in the test model successively, the jet flow aerodynamic force that is used to measure jet flow aerodynamic force is measured balance, total pressure measurement section, static pressure measurement section, wherein main force balance is connected with the air feed support arm with test model respectively.Jet flow system as the core component of this equipment, comprise secondary flow supply air line and main jet stream pipeline two parts, being laid in test model high-pressure air feed pipeline interior and in the air feed support arm respectively is connected, the corresponding high-pressure air feed pipeline that is connected with main jet stream pipeline with the secondary flow supply air line in the air feed support arm connects two high-pressure air feed flexible pipes respectively and connects the high-pressure air source pipeline through the air vent valve door, and the high-pressure air source pipeline is communicated with total pressure measurement section, static pressure measurement section and last model jet pipe successively by main jet stream pipeline; The high-pressure air source pipeline is communicated with the baroport of the outside nozzle of static pressure measurement section by the secondary flow supply air line.
Above-mentioned jet flow system and test model adopt the isolating construction form, and test model is replaceable.
It is six COMPONENT BALANCE that above-mentioned jet flow aerodynamic force is measured balance, can obtain the jet deflexion angle by handling.
The total pressure measurement rake is installed in the above-mentioned total pressure measurement section, four total pressure measurement pipes of total pressure measurement rake equal intervals distribution, the total pressure measurement pipe is always towards coming flow path direction.
Above-mentioned static pressure measurement section is straight sections such as nozzle exit, and long 23.5mm is at circumferentially uniform four baroports in order to measurement jet flow exit static pressure apart from edge, outlet 5mm place.
Above-mentioned secondary flow supply air line and main jet stream pipeline all adopt and reduce the corrugated tube that high pressure draught disturbs the jet flow balance.
Above-mentioned high-pressure air feed flexible pipe adopts diameter 38mm, can bear 40 atmospheric high-pressure air feed flexible pipes.
Above-mentioned air vent valve door all adopts maximum pressure 4MP, and its rear end all is connected on the corresponding high-pressure air feed pipeline, and the front end of pneumatic control valve door all is equipped with ring flange, can be connected with the high-pressure air feed flexible pipe.
The utility model is simple for structure, the parameter of main element obtains through pneumatic design or calculating, the flow parameter that secondary flow and main jet flow can accurately be controlled and measure simultaneously to installation, convenient disassembly, is applicable to the active Flow Control experiment of the various model Pneumatic methods realization of high-speed wind tunnel thrust deflexion.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Embodiment
A kind of experimental provision of realizing thrust deflexion comprises test model 1, main force balance 2, jet flow aerodynamic force measurement balance 3, total pressure measurement section 4, static pressure measurement section 5, jet flow system 6, high-pressure air feed flexible pipe 7, air vent valve door 8, air feed support arm 10.Described test model 1 connects air feed support arm 10, and is arranged in the wind-tunnel 15.Be laid with the main force balance 2 of measurement model aerodynamic force in the test model 1 successively, the jet flow aerodynamic force that is used to measure jet flow aerodynamic force is measured balance 3, total pressure measurement section 4, static pressure measurement section 5.Described main force balance 2 is connected with air feed support arm 10 with test model 1 respectively; It is six COMPONENT BALANCE that jet flow aerodynamic force is measured balance 3, can obtain the jet deflexion angle by handling; Total pressure measurement rake 13 is installed in the total pressure measurement section 4, and four total pressure measurement pipes 14 of 13 equal intervals distribution are harrowed in total pressure measurement, and total pressure measurement pipe 14 is always towards coming flow path direction; Static pressure measurement section 5 is straight sections such as nozzle exit, and long 23.5mm is at circumferentially uniform four baroports 9 in order to measurement jet flow exit static pressure apart from edge, outlet 5mm place.As the jet flow system 6 of the core component of this device, comprise secondary flow supply air line 11 and main jet stream pipeline 12 two parts, be laid in respectively in the test model, jet flow system 6 adopts the isolating construction form with empirical model 1, and empirical model 1 is replaceable.Supply air line 11 and main jet stream pipeline 12 high-pressure air feed pipelines corresponding and in the air feed support arm 10 are connected, connect two high-pressure air feed flexible pipes 7 with the secondary flow supply air line respectively with the corresponding high-pressure air feed pipeline that main jet stream pipeline is connected in the air feed support arm 10, connect the high-pressure air source pipeline through air vent valve door 8, the pneumatic control valve of high-pressure air source pipeline gases at high pressure by certain aperture behind the door, with corresponding pressure and flow, flow through total pressure measurement section 4, static pressure measurement section 5 and last model jet pipe successively by main jet stream pipeline 12 and flow out; Same high-pressure air source pipeline flows into baroport 9 with high pressure high energy air-flow by the circumferential slit aperture of the bleed pipe of static pressure measurement section 5 at last by secondary flow supply air line 11.Described secondary flow supply air line 11 and main jet stream pipeline 12 all adopt and reduce the corrugated tube that high pressure draught disturbs the jet flow balance; High-pressure air feed flexible pipe 7 adopts diameter 38mm, can bear 40 atmospheric high-pressure air feed flexible pipes; Air vent valve door 8 all adopts maximum pressure 4MP, and its rear end all is connected on the corresponding high-pressure air feed pipeline, and the front end of pneumatic control valve door all is equipped with ring flange, can be connected with the high-pressure air feed flexible pipe, and installation, convenient disassembly are easy to safeguard.This experimental facilities adopts the valve opening of industrial computer control pneumatic control valve 8, different flow value in the corresponding pipeline of different valve openings, the total pressure measurement of total pressure measurement section 4 rake 13 is connected with outside acquisition system with the baroport 9 of static pressure measurement section 5, the airstream data that obtains is also passed to industrial computer, so just formed a closed-loop control system, industrial computer constantly circulates and regulates control and measure calculating, till identical with the flow value of prior setting, carry out next step test operation again, be a kind of novel jet flow/jet active Flow Control experimental facilities of realizing that aircraft thrust turns to the high-speed wind tunnel test to design, its objective is by in jet flow, injecting a spot of high pressure draught, change the inner wave system of jet pipe, realize thrust deflexion, can accurately measure the flow and the pressure of secondary jet and jet flow simultaneously.
Claims (8)
1. experimental provision of realizing thrust deflexion, comprise and draw together test model (1), main force balance (2), jet flow aerodynamic force is measured balance (3), total pressure measurement section (4), static pressure measurement section (5), jet flow system (6), high-pressure air feed flexible pipe (7), air vent valve door (8), air feed support arm (10), it is characterized in that described test model (1) connects air feed support arm (10), and be arranged in the wind-tunnel (15), be laid with the main force balance (2) of measurement model aerodynamic force in the test model (1) successively, be used to measure the jet flow aerodynamic force measurement balance (3) of jet flow aerodynamic force, total pressure measurement section (4), static pressure measurement section (5), wherein main force balance (2) is connected with air feed support arm (10) with test model (1) respectively, jet flow system (6), comprise secondary flow supply air line (11) and main jet stream pipeline (12) two parts, being laid in test model (1) high-pressure air feed pipeline interior and in the air feed support arm (10) respectively is connected, the corresponding high-pressure air feed pipeline that is connected with main jet stream pipeline with the secondary flow supply air line in the air feed support arm (10) connects two high-pressure air feed flexible pipes (7) respectively and connects the high-pressure air source pipeline through air vent valve door (8), and the high-pressure air source pipeline flows pipeline (12) by main jet and is communicated with total pressure measurement section (4) successively, static pressure measurement section (5) and last model jet pipe; The high-pressure air source pipeline is communicated with the baroport (9) of the outside nozzle of static pressure measurement section (5) by secondary flow supply air line (11).
2. a kind of experimental provision of realizing thrust deflexion according to claim 1 is characterized in that described jet flow system (6) and test model (1) adopt the isolating construction form, and test model (1) is replaceable.
3. a kind of experimental provision of realizing thrust deflexion according to claim 1 is characterized in that it is six COMPONENT BALANCE that described jet flow aerodynamic force is measured balance (3), can obtain the jet deflexion angle by handling.
4. a kind of experimental provision of realizing thrust deflexion according to claim 1, it is characterized in that installing in the described total pressure measurement section (4) total pressure measurement rake (13), total pressure measurement rake (13) equal intervals distribution four total pressure measurement pipes (14), total pressure measurement pipe (14) is always towards coming flow path direction.
5. a kind of experimental provision of realizing thrust deflexion according to claim 1, it is characterized in that described static pressure measurement section (5) is straight sections such as nozzle exit, long 23.5mm is at circumferentially uniform four baroports (9) in order to measurement jet flow exit static pressure apart from edge, outlet 5mm place.
6. a kind of experimental provision of realizing thrust deflexion according to claim 1 is characterized in that described secondary flow supply air line (11) and main jet stream pipeline (12) is corrugated tube.
7. a kind of experimental provision of realizing thrust deflexion according to claim 1 is characterized in that described high-pressure air feed flexible pipe (7) adopts diameter 38mm, can bear 40 atmospheric high-pressure air feed flexible pipes.
8. a kind of experimental provision of realizing thrust deflexion according to claim 1, it is characterized in that described air vent valve door (8) all adopts maximum pressure 4MP, its rear end all is connected on the corresponding high-pressure air feed pipeline, the front end of pneumatic control valve door (8) all is equipped with ring flange, can be connected with high-pressure air feed flexible pipe (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220689525 CN203083804U (en) | 2012-12-14 | 2012-12-14 | Experiment device realizing thrust deflexion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220689525 CN203083804U (en) | 2012-12-14 | 2012-12-14 | Experiment device realizing thrust deflexion |
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| Publication Number | Publication Date |
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| CN203083804U true CN203083804U (en) | 2013-07-24 |
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| CN 201220689525 Expired - Fee Related CN203083804U (en) | 2012-12-14 | 2012-12-14 | Experiment device realizing thrust deflexion |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048110A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Experimental facility for realizing thrust deflexion and experimental technique thereof |
| CN107860554A (en) * | 2017-12-06 | 2018-03-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet Test Integrated model equipment and test method in wind tunnel test |
| CN108458852A (en) * | 2018-05-24 | 2018-08-28 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high-temperature tunnel quick changeable temperature potential device and alternating temperature voltage-transforming method |
| CN110455491A (en) * | 2019-09-11 | 2019-11-15 | 中国航空工业集团公司沈阳空气动力研究所 | Interior flow resistance force measuring method and device based on bellows balance system |
| CN112781827A (en) * | 2020-12-30 | 2021-05-11 | 中国航天空气动力技术研究院 | Ventilating support arm device applied to thrust measurement of vectoring nozzle and application |
| CN114509234A (en) * | 2022-04-20 | 2022-05-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flexible pipeline device for mixed heating gas jet flow gas supply of hypersonic wind tunnel |
| CN117073973A (en) * | 2023-10-17 | 2023-11-17 | 中国航空工业集团公司沈阳空气动力研究所 | Multifunctional double-culvert jet pipe wind tunnel test model |
-
2012
- 2012-12-14 CN CN 201220689525 patent/CN203083804U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048110A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Experimental facility for realizing thrust deflexion and experimental technique thereof |
| CN107860554A (en) * | 2017-12-06 | 2018-03-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet Test Integrated model equipment and test method in wind tunnel test |
| CN107860554B (en) * | 2017-12-06 | 2023-12-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet flow test integrated model device in wind tunnel test and test method |
| CN108458852A (en) * | 2018-05-24 | 2018-08-28 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high-temperature tunnel quick changeable temperature potential device and alternating temperature voltage-transforming method |
| CN108458852B (en) * | 2018-05-24 | 2024-03-29 | 中国航空工业集团公司沈阳空气动力研究所 | Rapid temperature and pressure changing device and temperature and pressure changing method for high-temperature wind tunnel |
| CN110455491A (en) * | 2019-09-11 | 2019-11-15 | 中国航空工业集团公司沈阳空气动力研究所 | Interior flow resistance force measuring method and device based on bellows balance system |
| CN112781827A (en) * | 2020-12-30 | 2021-05-11 | 中国航天空气动力技术研究院 | Ventilating support arm device applied to thrust measurement of vectoring nozzle and application |
| CN114509234A (en) * | 2022-04-20 | 2022-05-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Flexible pipeline device for mixed heating gas jet flow gas supply of hypersonic wind tunnel |
| CN117073973A (en) * | 2023-10-17 | 2023-11-17 | 中国航空工业集团公司沈阳空气动力研究所 | Multifunctional double-culvert jet pipe wind tunnel test model |
| CN117073973B (en) * | 2023-10-17 | 2023-12-12 | 中国航空工业集团公司沈阳空气动力研究所 | Multifunctional double-culvert jet pipe wind tunnel test 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: 20130724 Termination date: 20151214 |
|
| EXPY | Termination of patent right or utility model |