CN104859844A - Flap zero mass flow/jet flow control system - Google Patents
Flap zero mass flow/jet flow control system Download PDFInfo
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- CN104859844A CN104859844A CN201510260635.XA CN201510260635A CN104859844A CN 104859844 A CN104859844 A CN 104859844A CN 201510260635 A CN201510260635 A CN 201510260635A CN 104859844 A CN104859844 A CN 104859844A
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- wing flap
- flap
- jet
- flow
- cavity
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Abstract
The invention discloses a flap zero mass flow/jet flow control system, comprising a mass flow/jet flow generator, an air supply pipeline, a fuselage component, a wing component, a flap, a cavity and a gap. The fuselage component is connected with the wing component; the mass flow/jet flow generator and the air supply pipeline are positioned on the fuselage component; the mass flow/jet flow generator is connected with the air supply pipeline; the flap is positioned on the wing component; the cavity is formed in the flap; the gap is arranged on the leeside surface of the flap and communicated with the cavity. During work, the zero mass flow/jet flow generated by the zero mass flow/jet flow generator enters the cavity in the flap through the air supply pipeline, flows out from the leeside surface of the flap through the gap, and enters a flow field for flow control. By applying the flap zero mass flow/jet flow control system, the flaps flowing separation can be obviously improved, the lift coefficient is increased, and the stall angle of attack is delayed.
Description
Technical field
The present invention relates to aerodynamic scope, be specifically related to wing flap zero mass stream/jet flow control system.
Background technology
Modern active Flow Control technology mainly comprises two layers of meaning: one is " initiatively ", and namely when needs, local inputs a small amount of energy, can obtain non local or overall flowing change, aircraft performance is improved significantly; Two is " modern times ", and namely active Flow Control technology and modern information technologies, modern material technology, modern control technology, micro-electromechanical technology are combined closely.Modern active Flow Control technology can change the characteristic of Flow Field on the basis of not change of flight device profile, thus reaches the object of change of flight device aerodynamic characteristics.
In modern active Flow Control technology, jet is a kind of actv. flow control method, can effectively suppress aircraft flow separation, improve its flow characteristic.Zero-net-mass-flux jet adopts the crank motion of piston or piezoelectric membrane to blow/air absorbing body usually, becomes a series of collar vortex or vortex pair at narrow and small orifice profile, and these collar vortexs or vortex pair are mutually fused into a kind of momentum jet in abducent process; In air blowing process, layer Cavity Flow becomes collar vortex or vortex pair at orifice profile under the compression of piston or piezoelectric membrane, and moves to away from direction, aperture under their auto-induction effects; And in breathing process, collar vortex or vortex pair distance aperture comparatively far away and can not be inhaled in aperture, therefore, zero-net-mass-flux jet only has externally leaving momentum and output quality is the notable feature of zero.Flow compared with control with traditional blowing suction, the plurality of advantages such as zero-net-mass-flux jet has without the need to extra source of the gas, without the need to moving-member, simple and compact for structure, lightweight, cost is low, easy to maintenance, therefore receive the extensive concern of numerous researcher.
Summary of the invention
The present invention devises a kind of wing flap zero mass stream/jet flow control system, can realize wing flap separated flow control.
The technology used in the present invention is as follows: wing flap zero mass stream/jet flow control system, comprises mass flow/fluidic generator, supply air line, frame assembly, wing components, wing flap, cavity and seam road; Frame assembly is connected with wing components, and mass flow/fluidic generator and supply air line are positioned on frame assembly, and mass flow/fluidic generator is connected with supply air line, wing flap is positioned on wing components, wing flap inside has cavity, and seam road is arranged in wing flap lee face, and seam road communicates with cavity; During work, zero mass stream/jet that zero mass stream/fluidic generator produces is entered by supply air line in the cavity of wing flap inside, flows out from wing flap lee face through seam road, enters flow field and carries out flowing control.
The present invention also has following technical characteristic:
1, the flow control method adopted is zero mass stream or jet.
2, the seam road of wing flap zero mass stream/jet flow control system and wing flap lee face are at an angle; Stitch the position in road, angle and width to regulate according to flowing control effects demand; In supply air line, cavity, cross section is circle and diameter is identical.
3, seam road and wing flap lee face are acute angle.
The present invention can obviously improve wing flap flow separation, increases lift coefficient, postpones stalling incidence.
Accompanying drawing explanation
Fig. 1 is wing flap zero mass stream/jet flow control system figure;
Fig. 2 is wing flap A-A section-drawing.
Fig. 3 is the effect diagram that wing flap air blowing flowing controls to lift.
Detailed description of the invention
Further illustrate according to Figure of description citing below:
Wing flap zero mass stream/jet flow control system as shown in Figure 1-2, comprises mass flow/fluidic generator 1, supply air line 2, frame assembly 3, wing components 4, wing flap 5, cavity 6 and seam road 7; It is characterized in that, frame assembly 3 is connected with wing components 4, mass flow/fluidic generator 1 and supply air line 2 are positioned on frame assembly 3, mass flow/fluidic generator 1 is connected with supply air line 2, wing flap 5 is positioned on wing components 4, wing flap 5 inside has cavity 6, and seam road 7 is arranged in wing flap 5 lee face, and seam road 7 communicates with cavity 6; During work, zero mass stream/jet that zero mass stream/fluidic generator 1 produces is entered by supply air line 2 in the cavity 6 of wing flap 5 inside, flows out from wing flap 5 lee face through seam road 7, enters flow field and carries out flowing control.
The flow control method of wing flap zero mass stream/jet flow control system adopts zero mass stream or jet, and the two gets one, can not use simultaneously; The frequency of zero mass stream, peak velocity, the flowing such as speed, flow, the pressure controling parameters of jet can need to change according to flowing control.
Seam road 7 is arranged in wing flap 5 lee face, is generally arranged near wing flap 5 leading edge; Seam road 7 and wing flap 5 lee face are at an angle; Stitch the position in road 7, angle and width to need to regulate according to flowing control effects, generally, acute angle little is as far as possible selected, to promote flowing control effects with the angle of wing flap lee face in seam road 7.In supply air line 2, cross section is circular, adopts homalographic to design and try one's best to reduce inflection to reduce kinetic energy rejection; In cavity 6, cross section is also circular, and supply air line 2 internal diameter is identical with cavity 6 internal diameter, to reduce kinetic energy rejection during connection.
As shown in Figure 3, for certain aircraft wind tunnel test half module model, adopt this flow system, maximum lift coefficient 19.0% can be promoted, postpone stalling incidence 2.16 °.
Claims (4)
1. wing flap zero mass stream/jet flow control system, comprises mass flow/fluidic generator (1), supply air line (2), frame assembly (3), wing components (4), wing flap (5), cavity (6) and seam road (7); It is characterized in that, frame assembly (3) is connected with wing components (4), mass flow/fluidic generator (1) and supply air line (2) are positioned on frame assembly (3), mass flow/fluidic generator (1) is connected with supply air line (2), wing flap (5) is positioned on wing components (4), wing flap (5) inside has cavity (6), seam road (7) is arranged in wing flap (5) lee face, and seam road (7) communicates with cavity (6); During work, zero mass stream/jet that zero mass stream/fluidic generator (1) produces enters in the inner cavity (6) of wing flap (5) by supply air line (2), flow out from wing flap (5) lee face through seam road (7), enter flow field and carry out flowing control.
2. wing flap zero mass stream/jet flow control system according to claim 1, is characterized in that, the flow control method of employing is zero mass stream or jet.
3. wing flap zero mass stream/jet flow control system according to claim 1, is characterized in that, described seam road (7) and wing flap (5) lee face are at an angle; Stitch the position in road (7), angle and width to regulate according to flowing control effects demand; Described supply air line (2), cavity (6) interior cross section is circle and diameter is identical.
4. wing flap zero mass stream/jet flow control system according to claim 3, is characterized in that, seam road (7) and wing flap (5) lee face are acute angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510260635.XA CN104859844A (en) | 2015-05-16 | 2015-05-16 | Flap zero mass flow/jet flow control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510260635.XA CN104859844A (en) | 2015-05-16 | 2015-05-16 | Flap zero mass flow/jet flow control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104859844A true CN104859844A (en) | 2015-08-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510260635.XA Pending CN104859844A (en) | 2015-05-16 | 2015-05-16 | Flap zero mass flow/jet flow control system |
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| CN (1) | CN104859844A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248834A (en) * | 2016-11-06 | 2018-07-06 | 波音公司 | For the phase adjustment of resonant Flow device |
| CN111688892A (en) * | 2020-06-23 | 2020-09-22 | 西北工业大学 | Active flow control system for wing body fusion underwater glider |
| CN113251152A (en) * | 2021-04-29 | 2021-08-13 | 合肥工业大学 | Improved cavitation-resistant valve capable of reducing separation vortex |
| CN115180118A (en) * | 2022-08-02 | 2022-10-14 | 中国航空研究院 | High lift wing with joint jet flow control |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4600172A (en) * | 1984-01-09 | 1986-07-15 | Loth John L | Retractable rounded trailing edge for circulation control wing |
| RU2086468C1 (en) * | 1994-04-12 | 1997-08-10 | Сергей Владимирович Овсянников | Aerodynamic profile |
| US20070020099A1 (en) * | 2005-06-22 | 2007-01-25 | Us Of America As Represented By The Administrator Of The National Aeronautics & Space Administration | Noise reduction of aircraft flap |
| CN101323371A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Lift augmenter with united jet flow structure on wing flap |
| US20090050734A1 (en) * | 2006-09-06 | 2009-02-26 | Bae Systems Plc | Flow control actuators |
-
2015
- 2015-05-16 CN CN201510260635.XA patent/CN104859844A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4600172A (en) * | 1984-01-09 | 1986-07-15 | Loth John L | Retractable rounded trailing edge for circulation control wing |
| RU2086468C1 (en) * | 1994-04-12 | 1997-08-10 | Сергей Владимирович Овсянников | Aerodynamic profile |
| US20070020099A1 (en) * | 2005-06-22 | 2007-01-25 | Us Of America As Represented By The Administrator Of The National Aeronautics & Space Administration | Noise reduction of aircraft flap |
| US20090050734A1 (en) * | 2006-09-06 | 2009-02-26 | Bae Systems Plc | Flow control actuators |
| CN101323371A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Lift augmenter with united jet flow structure on wing flap |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248834A (en) * | 2016-11-06 | 2018-07-06 | 波音公司 | For the phase adjustment of resonant Flow device |
| CN111688892A (en) * | 2020-06-23 | 2020-09-22 | 西北工业大学 | Active flow control system for wing body fusion underwater glider |
| CN111688892B (en) * | 2020-06-23 | 2021-05-18 | 西北工业大学 | Active flow control system for wing body fusion underwater glider |
| CN113251152A (en) * | 2021-04-29 | 2021-08-13 | 合肥工业大学 | Improved cavitation-resistant valve capable of reducing separation vortex |
| CN113251152B (en) * | 2021-04-29 | 2024-01-12 | 合肥工业大学 | Improved generation reduces separation vortex anti-cavitation valve |
| CN115180118A (en) * | 2022-08-02 | 2022-10-14 | 中国航空研究院 | High lift wing with joint jet flow control |
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Application publication date: 20150826 |