CN108168831A - A kind of continuous change Mach number experiment supersonic wind tunnel - Google Patents
A kind of continuous change Mach number experiment supersonic wind tunnel Download PDFInfo
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- CN108168831A CN108168831A CN201711353624.1A CN201711353624A CN108168831A CN 108168831 A CN108168831 A CN 108168831A CN 201711353624 A CN201711353624 A CN 201711353624A CN 108168831 A CN108168831 A CN 108168831A
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- 230000007246 mechanism Effects 0.000 claims abstract description 9
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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Abstract
The present invention relates to a kind of continuous change Mach number test air tunnel, including wind-tunnel, adjustable plate, model supporting device and boundary layer partition board；Adjustable plate is connected to by motion control mechanism on the roof of hole, which can control to adjust plate and be moved up and down relative to hole roof, and also is able to control and regulation plate and is downwardly turned over relative to hole roof；Model supporting device is arranged on the lower face of adjustable plate, and as adjustable plate moves；Model supporting device is used to install model, and model supporting device can adjust the spatial attitude of model；The boundary layer partition board is arranged in parallel on wind-tunnel bottom wall, boundary layer partition board is used to that low speed flow to be isolated.The present invention is using the thought for directly carrying out flow field Mach number control and adjusting using uniform air flow after adjustable plate plane oblique shock wave in test section, and simple in structure, at low cost, continuous change Mach number response is fast, and rate of change adjustable extent is wide.
Description
Technical field
The present invention is a kind of continuous change Mach number (Ma) experiment supersonic wind tunnel, belongs to wind-tunnel technique field.
Background technology
The continuous pneumatic property for becoming Mach number wind tunnel test ability to conventional Ultrasound speed aircraft in acceleration and deceleration flight course
Energy research is most important, while the dynamic gas to the High Mach number aircraft using assembly power in power mode conversion process
The researchs such as dynamic characteristic are also of great significance.At this stage, conventional continuous change Mach number wind tunnel test, which is concentrated mainly on, passes through machinery
Regulating mechanism changes geometric shape, relative position or the specific heat ratio physics category by changing test section gas of wind tunnel nozzle component
Property carry out the methods of changing the Mach number of air-flow indirectly.For example, using rotation spray tube profiles, throat plug cone, nozzle contour are front and rear to be moved
It moves (to offset nozzle), flexible jet pipe, nozzle exit multistage stretch and are directly changed the side such as nozzle angle by mechanism
Method can be achieved to continuously adjust test section interior air-flow Mach number.Since wind tunnel nozzle belongs to very accurate component,
The minor change in air-driven type face is very big to Flow Field in Wind Tunnel qualitative effects, while jet pipe size is larger with respect to wind-tunnel agent structure, because
This such method is extremely complex in Design of Mechanical Structure and control etc., while cost price is also higher.And for passing through
Variable specific heat than mode come realize wind-tunnel it is continuous become Mach number method, although can directly utilize different tests gas specific heat ratio
Difference changes the pressure and temperature of fixed geometry nozzle exit, and then change Mach number, therefore structure is relatively simple, but its horse
Conspicuous number is adjusted that variation range is relatively narrow, while blends using different Working medium gas continuously to change the specific heat ratio physical attribute of gas
Caused aerodynamic characteristic influence is still not clear, additionally relates to storage, transport and recycling of corresponding special gas etc.
Various problems need to solve.Therefore there is an urgent need for exploring other more simple and practical continuous change Mach number test methods, to meet
Engineer application demand.
Invention content
Present invention is generally directed to traditional continuous Mach number wind tunnel test methods that become to need caused by adjustable jet tube venturi etc.
The problems such as complicated in mechanical structure, higher control accuracy and cost, with reference to how in test section using adjustable plate plane it is oblique
Uniform air flow directly carries out the thought of flow field Mach number control and adjusting after shock wave.
One kind of the present invention is continuous to become Mach number test air tunnel, including wind-tunnel, adjustable plate, model supporting device and boundary layer
Partition board；Adjustable plate is connected to by motion control mechanism on the roof of hole, the motion control mechanism can control to adjust plate relative to
Hole roof moves up and down, and also is able to control and regulation plate and is downwardly turned over relative to hole roof；Model supporting device is arranged on adjusting
The lower face of plate, and as adjustable plate moves；Model supporting device is used to install model, and model supporting device can adjust mould
The spatial attitude of type；The boundary layer partition board is arranged in parallel on wind-tunnel bottom wall, boundary layer partition board is used to that low speed flow to be isolated.
Further, the adjustable plate is trapezoidal plate.
Further, the trapezoidal plate small end of the adjustable plate is front end, and big end is overturning center.
The advantage of the invention is that：
1) it uses and directly carries out flow field Mach number control using uniform air flow after adjustable plate plane oblique shock wave in test section
Simple in structure with the thought of adjusting, at low cost, continuous to become Mach number response soon, rate of change adjustable extent is wide；
2) combination of translation+rotation is used in adjustable plate motion process, wall is first detached from before carrying out rotation and adjusting
Plate boundary layer region, it is ensured that after adjustable plate oblique shock wave wave can test area air-flow it is uniform；
3) using boundary layer baffle design near the position of wind-tunnel siding got in adjustable plate oblique shock wave, ensure adjustable plate
Generated oblique shock wave can be always got on the partition board in rotation process, eliminate it between wind-tunnel wall plate thickness boundary layer not
Profit interferes with each other, and the flow field structure in test section is excellent.It is matched simultaneously with used special trapezoidal adjustable plate, wind-tunnel can be optimized
Starting capability, flow field regions can be used by obtaining the most wide continuous range of Mach numbers and maximum of becoming.
Description of the drawings
Fig. 1 is the construction of wind tunnel schematic diagram of the present invention；
Fig. 2 is another schematic diagram of construction of wind tunnel of the present invention；
Wherein：Oblique shock wave position, 4- when 1- wind-tunnel bottom wall, 2- adjustable plates, 3- adjustable plates turn to different location are adjusted
Plate turns to different location example, 5- model supporting devices, 6- boundary layers partition board.
Specific embodiment
More particularly to a kind of continuous change Mach number test air tunnel, including wind-tunnel, adjustable plate, model supporting device and boundary layer
Partition board；Adjustable plate is connected to by motion control mechanism on the roof of hole, the motion control mechanism can control to adjust plate relative to
Hole roof moves up and down, and also is able to control and regulation plate and is downwardly turned over relative to hole roof；Model supporting device is arranged on adjusting
The lower face of plate, and as adjustable plate moves；Model supporting device is used to install model, and model supporting device can adjust mould
The spatial attitude of type；The boundary layer partition board is arranged in parallel on wind-tunnel bottom wall, boundary layer partition board is used to that low speed flow to be isolated；
The adjustable plate is trapezoidal plate；The trapezoidal short base of the adjustable plate is front end, and long base is overturning center；The length of adjustable plate
Base 1100mm, short base 600mm, trapezoidal high 1200mm；The downward maximum bottom offset ranging from 150mm of the adjustable plate.
Claims (5)
1. a kind of continuous change Mach number test air tunnel, including wind-tunnel, adjustable plate, model supporting device and boundary layer partition board；It adjusts
Plate is connected to by motion control mechanism on the roof of hole, the motion control mechanism can control to adjust plate relative to hole roof above and below
It is mobile, and also be able to control and regulation plate and downwardly turned over relative to hole roof；Model supporting device is arranged on the lower face of adjustable plate,
And as adjustable plate moves；Model supporting device is used to install model, and model supporting device can adjust the space appearance of model
State；The boundary layer partition board is arranged in parallel on wind-tunnel bottom wall, boundary layer partition board is used to that low speed flow to be isolated.
2. a kind of continuous change Mach number test air tunnel as described in claim 1, it is characterised in that：The adjustable plate is trapezoidal
Plate.
3. a kind of continuous change Mach number test air tunnel as described in claim 1, it is characterised in that：The adjustable plate it is trapezoidal short
Base is front end, and long base is overturning center.
4. a kind of continuous change Mach number test air tunnel as described in claim 1, it is characterised in that：The long base of adjustable plate
1100mm, short base 600mm, trapezoidal high 1200mm.
5. a kind of continuous change Mach number test air tunnel as described in claim 1, it is characterised in that：The adjustable plate it is downward
Maximum bottom offset ranging from 150mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711353624.1A CN108168831A (en) | 2017-12-15 | 2017-12-15 | A kind of continuous change Mach number experiment supersonic wind tunnel |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711353624.1A CN108168831A (en) | 2017-12-15 | 2017-12-15 | A kind of continuous change Mach number experiment supersonic wind tunnel |
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| CN108168831A true CN108168831A (en) | 2018-06-15 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110361156A (en) * | 2019-08-22 | 2019-10-22 | 湖北三江航天红阳机电有限公司 | A kind of test chamber inner core that Mach number is continuously adjustable |
| CN110530600A (en) * | 2019-07-30 | 2019-12-03 | 江苏理工学院 | A kind of atmospheric wind tunnel boundary layers thickness adjustment device and its control method |
| CN110940482A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Air-breathing type aircraft continuous variable Mach number force measurement test device |
| CN111487030A (en) * | 2020-06-04 | 2020-08-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Supersonic speed continuous variable Mach number nozzle based on center body |
| CN116086762A (en) * | 2023-03-06 | 2023-05-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-sound-velocity free jet test device for continuously changing Mach number in supersonic test |
| CN117589419A (en) * | 2024-01-18 | 2024-02-23 | 哈尔滨工业大学 | Rectifying device for simulating moving pavement of low-speed wind tunnel opening test section |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110530600A (en) * | 2019-07-30 | 2019-12-03 | 江苏理工学院 | A kind of atmospheric wind tunnel boundary layers thickness adjustment device and its control method |
| CN110530600B (en) * | 2019-07-30 | 2021-08-24 | 江苏理工学院 | Wind tunnel boundary layer thickness adjusting device and control method thereof |
| CN110361156A (en) * | 2019-08-22 | 2019-10-22 | 湖北三江航天红阳机电有限公司 | A kind of test chamber inner core that Mach number is continuously adjustable |
| CN110361156B (en) * | 2019-08-22 | 2021-05-18 | 湖北三江航天红阳机电有限公司 | Wind tunnel test section inner core with continuously adjustable Mach number |
| CN110940482A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Air-breathing type aircraft continuous variable Mach number force measurement test device |
| CN110940482B (en) * | 2019-11-13 | 2022-06-03 | 中国航天空气动力技术研究院 | Air-breathing type aircraft continuous variable Mach number force measurement test device |
| CN111487030A (en) * | 2020-06-04 | 2020-08-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Supersonic speed continuous variable Mach number nozzle based on center body |
| CN111487030B (en) * | 2020-06-04 | 2024-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Supersonic continuous Mach number variable spray pipe based on central body |
| CN116086762A (en) * | 2023-03-06 | 2023-05-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-sound-velocity free jet test device for continuously changing Mach number in supersonic test |
| CN116086762B (en) * | 2023-03-06 | 2023-06-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-sound-velocity free jet test device for continuously changing Mach number in supersonic test |
| CN117589419A (en) * | 2024-01-18 | 2024-02-23 | 哈尔滨工业大学 | Rectifying device for simulating moving pavement of low-speed wind tunnel opening test section |
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