CN103033334A - Testing device of flow measurement and control used in aerospace - Google Patents
Testing device of flow measurement and control used in aerospace Download PDFInfo
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- CN103033334A CN103033334A CN2012105524682A CN201210552468A CN103033334A CN 103033334 A CN103033334 A CN 103033334A CN 2012105524682 A CN2012105524682 A CN 2012105524682A CN 201210552468 A CN201210552468 A CN 201210552468A CN 103033334 A CN103033334 A CN 103033334A
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Abstract
The invention relates to a testing device of flow measurement and control used in aerospace. The testing device of flow measurement and control used in aerospace is composed of a flowmeter part and a control valve part. The control valve part drives a throttling device to move along a ball screw through a motor and a decelerator and controls the flow area inside a channel. A pitot-pressure rake and a static vent which are arranged on the flowmeter part are connected with such devices as external electron pressure scanning valve and the like, the flowmeter measures the total pressure and static pressure at the moment and figures out air flow in the channel of the moment. The testing device of flow measurement and control used in aerospace has the advantages that the structure is simple, parameters of primary elements are obtained through aerodynamic design or calculation, installment and disassembly are convenient, injection and extraction flow parameters are controlled and measured precisely, and the device can be used in tests in all air inlet channels of FL-3 wind tunnel.
Description
Technical field
The present invention relates to Aero-Space aerodynamic test technical field, particularly relate to the Aero-Space flow measurement control for air flow rate in the accurate control and measurement airplane intake model
Test unit processed.
Background technology
The air intake duct model test of aerospace flight vehicle is an important component part of wind tunnel test, it can effectively verify the performance of aircraft air intake duct, the test figure that matches with engine is provided, provides valuable reference for aspects such as air intake duct Stealth Fighter, minimizing Inlet drags simultaneously.And air intake test flow measurement and Control experiment equipment are the requisite test units of Aero-Space wind tunnel test, and it can provide the air intake test data effectively accurately.
Summary of the invention
The flow measurement of a kind of New Wind Tunnel air intake test and the opertaing device that the present invention be directed to Aero-Space wind-tunnel air intake test and design, its purpose is measured the interior stream flow of the air intake duct models such as aerospace flight vehicle, guided missile accurately and effectively.
The technical scheme that adopts is:
A kind of flow measurement of Aero-Space practicality and Control experiment device are comprised of flowmeter part and variable valve part two parts.Described flowmeter partly comprises straight section, screens, honeycomb, rearmounted screens, stagnation pressure rake, rectification contraction section, nozzle segment, baroport, the diffusers such as entrance, fiaring cone, rectification.Establish fiaring cone in the entrance, entrance is that point diameter is less,
The structure that the rear end diameter is larger, its rear end connect the straight sections such as rectification, and fiaring cone is fixed on its rear end between the straight sections such as entrance and rectification, and screens, honeycomb and rearmounted screens are installed in the straight section such as rectification successively.Described stagnation pressure rake has four, and circumferentially the uniform straight section rearward end such as rectification that is installed in has five stagnation pressure tubes on each stagnation pressure rake, is used for total pressure measurement.Rectification contraction section structure and entrance inverted configuration, its front end is connected with straight sections such as rectifications, and the rear end is connected with nozzle segment, be provided with successively three cross sections on the nozzle segment, four baroports of circumferential uniform installation on each cross section are used for flowmeter part static pressure measurement, and the nozzle segment rear end is connected with diffuser.Described variable valve partly comprises straight section, radome fairing, the throttling contraction sections such as rectification cap, supporting ring, ball-screw, zero position switch, restriction device, restriction portion, reductor, motor, throttling.Variable valve is partly by restriction portion front end connection traffic meter diffuser partly, the restriction portion rear end connects the straight section front ends such as throttling, the straight section rear ends such as throttling connect the throttling contraction section, the in-built restriction device of the straight section such as restriction portion and throttling, restriction device connects motor by reductor, the ball-screw front end is supported on the supporting ring that the restriction portion front end is equipped with, the ball-screw rear end connects restriction device, motor via reducer drives restriction device and moves forward and backward along ball-screw, forms circulation area control with restriction portion.The entrance of described flowmeter part connects the air intake duct model, and the throttling contraction section of variable valve part connects the wind-tunnel Outer Tube, consists of a kind of flow measurement and Control experiment device of Aero-Space practicality.
The straight sections such as the straight sections such as the straight sections such as above-mentioned entrance and rectification, rectification and rectification contraction section, rectification contraction section and the straight sections such as nozzle segment, nozzle segment and diffuser, diffuser and restriction portion, restriction portion and throttling, throttling and throttling contraction section are connected and fixed by flange and bolt and seal with O type circle.
Above-mentioned rectification cap is connected to the restriction device front end, is used for reducing the flow-disturbing effect of ball-screw.
Above-mentioned zero position switch is contained on the restriction portion outer wall, is used for the stroke of spacing restriction device.
Outside the above-mentioned radome fairing cover dress throttling contraction section, prevent variable valve part rear end burbling.
The present invention is simple for structure, and the parameter of main element obtains through pneumatic design or calculating, installs, convenient disassembly, and the accurate control and measurement flow parameter injecting or extract out simultaneously is applicable to the various air intake tests of wind-tunnel.
Description of drawings
Fig. 1 is structural representation of the present invention.
Embodiment
A kind of flow measurement of Aero-Space practicality and Control experiment device partly are comprised of flowmeter part and variable valve.Described flowmeter partly comprises the straight sections 3 such as entrance 1, fiaring cone 2, rectification, screens 4, honeycomb 5, rearmounted screens 6, stagnation pressure rake 7, rectification contraction section 8, nozzle segment 9, baroport 10, diffuser 11.Establish fiaring cone 2 in the entrance 1, entrance 1 is that point diameter is less, the structure that the rear end diameter is larger, its rear end connects the straight sections 3 such as rectification, cooperate with fiaring cone 2, can effectively reduce air-flow velocity, prevent burbling, thereby obtain the more air-flow of uniformity in the total pressure measurement section, improve measuring accuracy.Fiaring cone 2 is fixed between the straight sections 3 such as entrance 1 and rectification with its rear end, screens 4, honeycomb 5 and rearmounted screens 6 are installed in the straight sections 3 such as rectification successively, their effect is to break up large vortex air flow, and it is more even that air-flow is distributed, and is convenient to follow-up Measurement accuracy.Rectification contraction section 8 front ends are connected with straight sections 3 such as rectifications, the rear end is connected with nozzle segment 9, is provided with successively three cross sections on the nozzle segment 9, four baroports 10 of circumferential uniform installation on each cross section, be used for flowmeter part static pressure measurement, nozzle segment 9 rear ends are connected with diffuser 11.Described variable valve partly comprises straight section 20, radome fairing 21, the throttling contraction sections 22 such as rectification cap 12, supporting ring 13, ball-screw 14, zero position switch 15, restriction device 16, restriction portion 17, reductor 18, motor 19, throttling.Variable valve is partly by restriction portion 17 front end connection traffic meters diffuser 11 partly, restriction portion 17 rear ends connect straight section 20 front ends such as throttling, the straight sections such as throttling 20 rear ends connect throttling contraction section 22, the straight section 20 in-built restriction devices 16 such as restriction portion 17 and throttling, restriction device 16 front ends are equipped with the rectification cap, are used for reducing the flow-disturbing effect of ball-screw.Restriction device 16 connects motor 19 by reductor 18, ball-screw 14 front ends are supported on the supporting ring 13 that restriction portion 17 front ends are equipped with, ball-screw 14 rear ends connect restriction device 16, motor 19 drives restriction device 16 by reductor 18 and moves forward and backward along ball-screw 14, form circulation area control with restriction portion, and then the air flow rate in the control flowmeter, on the restriction portion outer wall zero position switch is housed, the stroke that is used for spacing restriction device prevents that restriction device 16 and restriction portion 17 from colliding.Radome fairing 21 is to prevent variable valve part back segment burbling.The straight sections such as straight section 3, rectification 3 such as described entrance 1 and rectification are connected and fixed by flange and bolt and seal with O type circle with the straight sections such as straight section 20, throttling such as restriction portion 17, restriction portion 17 and throttling 20 and throttling contraction section 22 with diffuser 11, diffuser 11 with nozzle segment 9, nozzle segment 9 with rectification contraction section 8, rectification contraction section 8, install like this, dismounting is quick and convenient, be easy to safeguard.The entrance 1 of described flowmeter part connects the air intake duct model, and the throttling contraction section 22 of variable valve part connects the wind-tunnel Outer Tube.Consist of a kind of flow measurement and Control experiment device of Aero-Space practicality.
Principle of work
Claims (5)
1. the flow measurement of an Aero-Space practicality and Control experiment device, partly formed by flowmeter part and variable valve, it is characterized in that described flowmeter partly comprises entrance (1), fiaring cone (2), the straight sections such as rectification (3), screens (4), honeycomb (5), rearmounted screens (6), stagnation pressure rake (7), rectification contraction section (8), nozzle segment (9), baroport (10), diffuser (11), establish fiaring cone (2) in the entrance (1), entrance (1) is that point diameter is less, the structure that the rear end diameter is larger, its rear end connects the straight sections (3) such as rectification, fiaring cone (2) is fixed between the straight sections (3) such as entrance (1) and rectification with its rear end, screens (4), honeycomb (5) and rearmounted screens (6) are installed in the straight sections (3) such as rectification successively, stagnation pressure rake (7) has four, circumferential uniform straight section (3) rearward end such as rectification that is installed in, on each stagnation pressure rake five stagnation pressure tubes are arranged, be used for total pressure measurement, rectification contraction section (8) structure and entrance (1) inverted configuration, its front end is connected with straight sections (3) such as rectifications, the rear end is connected with nozzle segment (9), be provided with successively three cross sections on the nozzle segment (9), circumferential four baroports of uniform installation (10) on each cross section, be used for flowmeter part static pressure measurement, nozzle segment (9) rear end is connected with diffuser (11); Described variable valve partly comprises rectification cap (12), supporting ring (13), ball-screw (14), zero position switch (15), restriction device (16), restriction portion (17), reductor (18), motor (19), the straight sections such as throttling (20), radome fairing (21), throttling contraction section (22), variable valve is partly by restriction portion (17) front end connection traffic meter diffuser (11) partly, restriction portion (17) rear end connects straight section (20) front ends such as throttling, the straight sections such as throttling (20) rear end connects throttling contraction section (22), the in-built restriction devices of straight section (20) (16) such as restriction portion (17) and throttling, restriction device (16) connects motor (19) by reductor (18), ball-screw (14) front end is supported on the supporting ring (13) that restriction portion (17) front end is equipped with, ball-screw (14) rear end connects restriction device (16), motor (19) drives restriction device (16) by reductor (18) and moves forward and backward along ball-screw (14), form circulation area control with restriction portion, the entrance (1) of described flowmeter part connects the air intake duct model, and the throttling contraction section (22) of variable valve part connects the wind-tunnel Outer Tube.
2. the flow measurement of a kind of Aero-Space practicality according to claim 1 and Control experiment device is characterized in that the straight sections (3) such as straight section (3), rectification such as described entrance (1) and rectification and rectification contraction section (8), rectification contraction section (8) are connected and fixed by flange and bolt and seal with O type circle with the straight sections (20) such as straight section (20), throttling such as restriction portion (17), restriction portion (17) and throttling and throttling contraction section (22) with diffuser (11), diffuser (11) with nozzle segment (9), nozzle segment (9).
3. the flow measurement of a kind of Aero-Space practicality according to claim 1 and Control experiment device is characterized in that described rectification cap (12) is connected to restriction device (16) front end.
4. the flow measurement of a kind of Aero-Space practicality according to claim 1 and Control experiment device is characterized in that described zero position switch (15) is contained on restriction portion (17) outer wall.
5. the flow measurement of a kind of Aero-Space practicality according to claim 1 and Control experiment device is characterized in that outside described radome fairing (21) the cover dress throttling contraction section (22).
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| CN2012105524682A CN103033334A (en) | 2012-12-19 | 2012-12-19 | Testing device of flow measurement and control used in aerospace |
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| CN2012105524682A CN103033334A (en) | 2012-12-19 | 2012-12-19 | Testing device of flow measurement and control used in aerospace |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104266817A (en) * | 2014-09-17 | 2015-01-07 | 北京动力机械研究所 | Air inlet channel test throttling cone |
| CN104340377A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Static vent shaping bulge of light airplane |
| CN104848904A (en) * | 2015-06-05 | 2015-08-19 | 中国航天空气动力技术研究院 | Air duct flow measuring system |
| CN104949816A (en) * | 2015-07-17 | 2015-09-30 | 中国空气动力研究与发展中心低速空气动力研究所 | Flow control device for low-speed wind tunnel TPS experiment |
| CN105465028A (en) * | 2016-01-05 | 2016-04-06 | 农业部南京农业机械化研究所 | Flow regulating device for ventilator testing and using method of flow regulating device |
| CN106092494A (en) * | 2016-05-26 | 2016-11-09 | 中国人民解放军63820部队吸气式高超声速技术研究中心 | Drive aircraft pushes away resistance characteristic world conversion method |
| CN106441781A (en) * | 2016-09-12 | 2017-02-22 | 中国人民解放军国防科学技术大学 | Flow rate measurable air intake duct throttling device |
| CN107830986A (en) * | 2017-11-29 | 2018-03-23 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of air intake duct model flow control device |
| CN107917793A (en) * | 2017-11-14 | 2018-04-17 | 中国空气动力研究与发展中心高速空气动力研究所 | The multiple rows of pressure measurement rake device of one kind experiment |
| CN109128715A (en) * | 2018-10-15 | 2019-01-04 | 北京动力机械研究所 | The preparation method of water cooling jet pipe measurement segment structure under big gas flow use condition |
| CN111912596A (en) * | 2020-07-27 | 2020-11-10 | 西北工业大学 | Small-sized straight-flow wind tunnel diffusion section with ultra-long fairing and annular separation-preventing net |
| CN112197826A (en) * | 2020-09-02 | 2021-01-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Air inlet mass flow measuring device and measuring method for aircraft engine |
| CN112903232A (en) * | 2021-01-22 | 2021-06-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Flow regulating device for wind tunnel test of aircraft atmospheric data system |
| CN114235263A (en) * | 2021-11-30 | 2022-03-25 | 中国航发沈阳发动机研究所 | Static pressure measuring device and method for measuring static pressure in aircraft engine flow passage |
| CN115031919A (en) * | 2022-08-10 | 2022-09-09 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel two-throat channel |
| CN116088593A (en) * | 2023-04-12 | 2023-05-09 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Low-temperature wind tunnel liquid nitrogen jet bent frame flow control method, device and storage medium |
| CN115596693B (en) * | 2022-09-02 | 2024-04-16 | 中国电子科技集团公司第三十八研究所 | Performance test system and method of centrifugal fan in near space simulation environment |
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Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104340377A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Static vent shaping bulge of light airplane |
| CN104340377B (en) * | 2013-08-05 | 2016-09-28 | 哈尔滨飞机工业集团有限责任公司 | A kind of baroport correction of the flank shape bulge of light aerocraft |
| CN104266817A (en) * | 2014-09-17 | 2015-01-07 | 北京动力机械研究所 | Air inlet channel test throttling cone |
| CN104848904B (en) * | 2015-06-05 | 2018-08-07 | 中国航天空气动力技术研究院 | Inlet duct flow system for measuring quantity |
| CN104848904A (en) * | 2015-06-05 | 2015-08-19 | 中国航天空气动力技术研究院 | Air duct flow measuring system |
| CN104949816A (en) * | 2015-07-17 | 2015-09-30 | 中国空气动力研究与发展中心低速空气动力研究所 | Flow control device for low-speed wind tunnel TPS experiment |
| CN104949816B (en) * | 2015-07-17 | 2017-11-28 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of volume control device for low-speed wind tunnel TPS experiments |
| CN105465028A (en) * | 2016-01-05 | 2016-04-06 | 农业部南京农业机械化研究所 | Flow regulating device for ventilator testing and using method of flow regulating device |
| CN106092494A (en) * | 2016-05-26 | 2016-11-09 | 中国人民解放军63820部队吸气式高超声速技术研究中心 | Drive aircraft pushes away resistance characteristic world conversion method |
| CN106441781A (en) * | 2016-09-12 | 2017-02-22 | 中国人民解放军国防科学技术大学 | Flow rate measurable air intake duct throttling device |
| CN106441781B (en) * | 2016-09-12 | 2018-10-23 | 中国人民解放军国防科学技术大学 | A kind of measurable air intake duct throttling set of flow |
| CN107917793A (en) * | 2017-11-14 | 2018-04-17 | 中国空气动力研究与发展中心高速空气动力研究所 | The multiple rows of pressure measurement rake device of one kind experiment |
| CN107830986A (en) * | 2017-11-29 | 2018-03-23 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of air intake duct model flow control device |
| CN109128715A (en) * | 2018-10-15 | 2019-01-04 | 北京动力机械研究所 | The preparation method of water cooling jet pipe measurement segment structure under big gas flow use condition |
| CN111912596A (en) * | 2020-07-27 | 2020-11-10 | 西北工业大学 | Small-sized straight-flow wind tunnel diffusion section with ultra-long fairing and annular separation-preventing net |
| CN112197826A (en) * | 2020-09-02 | 2021-01-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Air inlet mass flow measuring device and measuring method for aircraft engine |
| CN112903232A (en) * | 2021-01-22 | 2021-06-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Flow regulating device for wind tunnel test of aircraft atmospheric data system |
| CN114235263A (en) * | 2021-11-30 | 2022-03-25 | 中国航发沈阳发动机研究所 | Static pressure measuring device and method for measuring static pressure in aircraft engine flow passage |
| CN114235263B (en) * | 2021-11-30 | 2024-03-19 | 中国航发沈阳发动机研究所 | Static pressure measuring device and method for measuring static pressure in flow passage of aero-engine |
| CN115031919A (en) * | 2022-08-10 | 2022-09-09 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel two-throat channel |
| CN115031919B (en) * | 2022-08-10 | 2022-11-01 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel two-throat channel |
| CN115596693B (en) * | 2022-09-02 | 2024-04-16 | 中国电子科技集团公司第三十八研究所 | Performance test system and method of centrifugal fan in near space simulation environment |
| CN116088593A (en) * | 2023-04-12 | 2023-05-09 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Low-temperature wind tunnel liquid nitrogen jet bent frame flow control method, device and storage medium |
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Application publication date: 20130410 |