CN104527965B - Symmetrical airfoil comprehensive moving end-wall surface current autocontrol system - Google Patents
Symmetrical airfoil comprehensive moving end-wall surface current autocontrol system Download PDFInfo
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- CN104527965B CN104527965B CN201410765737.2A CN201410765737A CN104527965B CN 104527965 B CN104527965 B CN 104527965B CN 201410765737 A CN201410765737 A CN 201410765737A CN 104527965 B CN104527965 B CN 104527965B
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- rotating shaft
- symmetrical airfoil
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Abstract
A kind of symmetrical airfoil comprehensive moving end-wall surface current autocontrol system, including false wing panel, lower axle, lower tightening nut, balance tightening nut and symmetrical airfoil measuring section under false on leading edge moving end-wall surface current autocontrol system, lee face moving end-wall surface current autocontrol system, upper stretching screw, upper shaft, symmetrical airfoil wing panel, axis, balance mounting seat, positive and negative nut, balance, balance tapered sleeve, symmetrical airfoil；Under symmetrical airfoil, false wing panel is installed on lower axle, symmetrical airfoil is measured with symmetrical airfoil after false wing panel locking under false wing panel and symmetrical airfoil and intersegmental all leaves gap；Symmetrical airfoil measuring section leading edge is provided with leading edge rotating shaft, and the upper end of leading edge rotating shaft is installed in leading edge rotating shaft in mounting seat by the first deep groove ball bearing, and the lower end of leading edge rotating shaft is installed under leading edge rotating shaft in mounting seat by the second deep groove ball bearing.The present invention has preferably flowing and controls effect, can realize symmetrical airfoil five component aerodynamic load simultaneously and measure.
Description
Technical field
The present invention relates to a kind of symmetrical airfoil comprehensive moving end-wall surface current autocontrol system.
Background technology
Active Flow Control technology is a kind of emerging important technology, it has also become the forward position of aerodynamic development,
Its development and application will bring major transformation to future aircraft design.Active Flow Control technology is in flow field
Directly apply suitable disturbance and be coupled to realize the control to flowing with flow field, it is advantageous that it can need
The time wanted and position occur, by the energy input of local, it is thus achieved that change of effectively flowing locally or globally,
And then make the flying quality of aircraft significantly improve.
Summary of the invention
For problem above, the open a kind of symmetrical airfoil comprehensive moving end-wall surface current autocontrol system of the present invention, including
Leading edge moving end-wall surface current autocontrol system, lee face moving end-wall surface current autocontrol system, upper stretching screw, upper shaft,
False wing panel, axis, balance mounting seat, positive and negative nut, balance, balance tapered sleeve, symmetrical airfoil on symmetrical airfoil
Lower false wing panel, lower axle, lower tightening nut, balance tightening nut and symmetrical airfoil measuring section；Described leading edge moves
Wall flow autocontrol system includes mounting seat in leading edge rotating shaft, the first deep groove ball bearing, leading edge rotating shaft, second deep
Mounting seat under ditch ball bearing, leading edge rotating shaft shaft coupling, leading edge rotating shaft electric motor and leading edge rotating shaft；Described lee face moves
Dynamic wall flow autocontrol system includes mounting seat under lee face rotating shaft electric motor, lee face rotating shaft, lee face rotating shaft connection
Mounting seat in axial organ, the 3rd deep groove ball bearing, lee face rotating shaft, the 4th deep groove ball bearing and lee face rotating shaft；
On symmetrical airfoil, false wing panel is installed in upper shaft, and by upper tension screw lock, false wing panel peace under symmetrical airfoil
It is loaded on lower axle, and is locked by lower tightening nut, false wing panel lock under false wing panel and symmetrical airfoil on symmetrical airfoil
Intersegmental with symmetrical airfoil measurement after tight all leave gap；Symmetrical airfoil measuring section leading edge is provided with leading edge rotating shaft, front
The upper end of edge rotating shaft is installed in leading edge rotating shaft in mounting seat by the first deep groove ball bearing, the lower end of leading edge rotating shaft
It is installed under leading edge rotating shaft in mounting seat by the second deep groove ball bearing；Leading edge rotating shaft lower end is joined by leading edge rotating shaft
Axial organ is connected with leading edge rotating shaft electric motor；Balance mounting seat is positioned at symmetrical airfoil measuring section, and is connected with axis,
It gentle balance mounting seat is connected by positive and negative nut, and is locked by balance tapered sleeve and balance tightening nut, balance
Measuring end to be connected with symmetrical airfoil measuring section, balance strut ends is by axis and vacation wing panel and symmetry on symmetrical airfoil
Under aerofoil profile, false wing panel connects；Lee face rotating shaft upper end is installed in lee face rotating shaft peace by the 4th deep groove ball bearing
In dress seat, lee face rotating shaft lower end is installed under lee face rotating shaft in mounting seat by the 3rd deep groove ball bearing, the back of the body
Rotating shaft lower end, wind face is connected with lee face rotating shaft electric motor by lee face rotating shaft shaft coupling.
The present invention also has a following technical characteristic:
1, the lee face spindle central of described lee face moving end-wall surface current autocontrol system away from 0.52 times of chord length of leading edge, away from
0.036 times of chord length of the symmetrical airfoil plane of symmetry, lee face shaft radius is 0.036 times of chord length.
2, when leading edge moving end-wall surface current autocontrol system or the wall linear velocity of lee face moving end-wall surface current autocontrol system
During more than or equal to the twice of speed of incoming flow, system can delay symmetrical airfoil stall.
3, described balance is five component aerodynamic strain balances, balance measurement end and symmetrical airfoil measuring section phase
Even street, under the strut ends of balance wing panel, symmetrical airfoil false with on symmetrical airfoil respectively, false wing panel is connected, sky
Flat measure end and strut ends is not joined directly together, ensure on symmetrical airfoil under false wing panel and symmetrical airfoil false
The power of wing panel can guarantee that the two-dimensional flow of symmetrical airfoil, energy while being not transmitted on symmetrical airfoil measuring section
Enough realize symmetrical airfoil measuring section five component aerodynamic load to measure.
Beneficial effects of the present invention and advantage:
The present invention is by leading edge moving end-wall surface current autocontrol system and lee face moving end-wall surface current autocontrol system
The integrated application of two set control systems realizes coupling relative to position, wall linear velocity symmetrical airfoil with speed of incoming flow
The determination of relation, has preferably flowing and controls effect, can realize symmetrical airfoil five component air force simultaneously
Load measurement.
Accompanying drawing explanation
Fig. 1 symmetrical airfoil comprehensive moving end-wall surface current autocontrol system structure chart；
Fig. 2 symmetrical airfoil comprehensive moving end-wall surface current autocontrol system A-A profile；
Fig. 3 symmetrical airfoil comprehensive moving end-wall surface current autocontrol system B-B profile；
Fig. 4 symmetrical airfoil comprehensive moving end-wall surface current autocontrol system C-C profile；
Detailed description of the invention
Further illustrate below according to accompanying drawing citing:
Embodiment 1
As it is shown in figure 1, a kind of symmetrical airfoil comprehensive moving end-wall surface current autocontrol system, including upper stretching screw 1,
False wing panel 3, axis 4, balance mounting seat 8, positive and negative nut 9, balance 10, sky on upper shaft 2, symmetrical airfoil
False wing panel 16, lower axle 17, lower tightening nut 18, balance tightening nut 19 under flat tapered sleeve 11, symmetrical airfoil
With symmetrical airfoil measuring section 25, native system also includes that leading edge moving end-wall surface current autocontrol system and lee face move
Wall flow autocontrol system；Leading edge moving end-wall surface current autocontrol system includes mounting seat 5, first in leading edge rotating shaft
Deep groove ball bearing 6, leading edge rotating shaft the 7, second deep groove ball bearing 12, leading edge rotating shaft shaft coupling 13, leading edge rotating shaft
Mounting seat 15 under motor 14 and leading edge rotating shaft；Lee face moving end-wall surface current autocontrol system includes lee face rotating shaft
Mounting seat 21 under motor 20, lee face rotating shaft, lee face rotating shaft shaft coupling the 22, the 3rd deep groove ball bearing 23,
Mounting seat 27 on lee face rotating shaft the 24, the 4th deep groove ball bearing 26 and lee face rotating shaft；The false wing on symmetrical airfoil
Section 3 is installed in upper shaft 2, and is locked by upper stretching screw 1, and under symmetrical airfoil, false wing panel 16 is installed on
On lower axle 17, and locked by lower tightening nut 18, the false wing under false wing panel 3 and symmetrical airfoil on symmetrical airfoil
Gap is all left after section 16 locking and between symmetrical airfoil measuring section 25；Symmetrical airfoil measuring section 25 leading edge is installed
Having leading edge rotating shaft 7, the upper end of leading edge rotating shaft 7 is installed in leading edge rotating shaft installation by the first deep groove ball bearing 6
In seat 5, the lower end of leading edge rotating shaft 7 is installed on mounting seat 15 under leading edge rotating shaft by the second deep groove ball bearing 12
In；Leading edge rotating shaft 7 lower end is connected with leading edge rotating shaft electric motor 14 by leading edge rotating shaft shaft coupling 13；Balance is installed
Seat 8 is positioned at symmetrical airfoil measuring section 25, and is connected with axis 4, and balance 10 and balance mounting seat 8 are by just
Anti-nut 9 connects, and is locked by balance tapered sleeve 11 and balance tightening nut 19, balance 10 measure end with
Symmetrical airfoil measuring section 25 connects, and balance 10 strut ends is by vacation wing panel 3 on axis 4 and symmetrical airfoil and right
False wing panel 16 under aerofoil profile is claimed to connect；Lee face rotating shaft 24 upper end is installed on the back of the body by the 4th deep groove ball bearing 26
In the rotating shaft of wind face in mounting seat 27, lee face rotating shaft 24 lower end is installed on the back of the body by the 3rd deep groove ball bearing 23
Under the rotating shaft of wind face in mounting seat 21, lee face rotating shaft shaft coupling 22 is passed through with leeward in lee face rotating shaft 24 lower end
Face rotating shaft electric motor 20 connects.
It is disposed with two set moving end-wall surface current autocontrol systems in symmetrical airfoil measuring section leading edge and lee face, is respectively
Leading edge moving end-wall surface current autocontrol system and lee face moving end-wall surface current autocontrol system, two set moving end-wall surface currents move
Control system can be used alone, it is also possible to use simultaneously, can either use as passive flow control apparatus,
Can be used as active flow control devices to use.
Embodiment 2
Moving end-wall surface current autocontrol system is defined below with the relative position of symmetrical airfoil:
The leading edge of leading edge moving end-wall surface current autocontrol system is concordant with symmetrical airfoil vacation wing panel leading edge, leading edge rotating shaft half
Footpath is 0.05 times of chord length；This design does not change the chord length of symmetrical airfoil, and is destroying symmetrical airfoil profile and reality
Now flowing control aspect has well balance.The lee face spindle central of lee face moving end-wall surface current autocontrol system
Away from 0.52 times of chord length of leading edge, away from 0.036 times of chord length of the symmetrical airfoil plane of symmetry, lee face shaft radius is 0.036
Times chord length；This is designed to control to cut both ways with active Flow Control in passive flowing.
Embodiment 3
The wall linear velocity of cylindrical shaft with the coupled relation of speed of incoming flow is:
When the wall linear velocity of moving end-wall surface current autocontrol system is more than or equal to speed of incoming flow, to symmetrical airfoil
Lee face flow separation control is effective；When the wall linear velocity of moving end-wall surface current autocontrol system is more than or equal to
During the twice of speed of incoming flow, control effect clearly, can effectively separation delay, delay symmetrical airfoil stall.
Embodiment 4
Symmetrical airfoil five component aerodynamic load metering system is as follows:
Being disposed with five component aerodynamic strain balances inside symmetrical airfoil measuring section, balance measurement end is with symmetrical
Aerofoil profile measuring section is connected, and under balance strut ends wing panel, symmetrical airfoil false with on symmetrical airfoil, false wing panel is connected, sky
Flat measurement end and strut ends are not joined directly together, and are ensureing on symmetrical airfoil the false wing under false wing panel and symmetrical airfoil
The power of section can guarantee that the two-dimensional flow of symmetrical airfoil while being not transmitted on symmetrical airfoil measuring section, it is possible to realizes
Symmetrical airfoil measuring section five component aerodynamic load is measured.
Claims (5)
1. a symmetrical airfoil comprehensive moving end-wall surface current autocontrol system, including upper stretching screw (1), upper shaft (2), symmetry
False wing panel (3), axis (4), balance mounting seat (8), positive and negative nut (9), balance (10), balance in aerofoil profile
False wing panel (16), lower axle (17), lower tightening nut (18), balance tension spiral shell under tapered sleeve (11), symmetrical airfoil
Female (19) and symmetrical airfoil measuring section (25)；It is characterized in that, also include leading edge moving end-wall surface current autocontrol system,
Lee face moving end-wall surface current autocontrol system；Described leading edge moving end-wall surface current autocontrol system includes pacifying in leading edge rotating shaft
Dress seat (5), the first deep groove ball bearing (6), leading edge rotating shaft (7), the second deep groove ball bearing (12), leading edge rotating shaft
Mounting seat (15) under shaft coupling (13), leading edge rotating shaft electric motor (14) and leading edge rotating shaft；Described lee face moving end-wall
Surface current autocontrol system includes that under lee face rotating shaft electric motor (20), lee face rotating shaft, mounting seat (21), lee face turn
Axle shaft coupling (22), the 3rd deep groove ball bearing (23), lee face rotating shaft (24), the 4th deep groove ball bearing (26)
With mounting seat (27) in lee face rotating shaft；On symmetrical airfoil, false wing panel (3) is installed in upper shaft (2), and passes through
Upper stretching screw (1) is locked, and under symmetrical airfoil, false wing panel (16) is installed on lower axle (17), and by drop-down
Jack panel (18) is locked, with right after on symmetrical airfoil, under false wing panel (3) and symmetrical airfoil, false wing panel (16) is locked
Claim all to leave gap between aerofoil profile measuring section (25)；Symmetrical airfoil measuring section (25) leading edge is provided with leading edge rotating shaft (7),
The upper end of leading edge rotating shaft (7) is installed in leading edge rotating shaft in mounting seat (5) by the first deep groove ball bearing (6),
It is interior that the lower end of leading edge rotating shaft (7) is installed on mounting seat (15) under leading edge rotating shaft by the second deep groove ball bearing (12)；
Leading edge rotating shaft (7) lower end is connected with leading edge rotating shaft electric motor (14) by leading edge rotating shaft shaft coupling (13)；It safety
Dress seat (8) is positioned at symmetrical airfoil measuring section (25), and is connected with axis (4), balance (10) and balance
Mounting seat (8) is connected by positive and negative nut (9), and by balance tapered sleeve (11) and balance tightening nut (19)
Locking, balance (10) is measured end and is connected with symmetrical airfoil measuring section (25), during balance (10) strut ends is passed through
Under axle (4) wing panel (3) false with on symmetrical airfoil and symmetrical airfoil, false wing panel (16) is connected；Lee face rotating shaft (24)
Upper end is installed in lee face rotating shaft in mounting seat (27) by the 4th deep groove ball bearing (26), lee face rotating shaft
(24) lower end is installed under lee face rotating shaft in mounting seat (21) by the 3rd deep groove ball bearing (23), leeward
Face rotating shaft (24) lower end is connected with lee face rotating shaft electric motor (20) by lee face rotating shaft shaft coupling (22).
A kind of symmetrical airfoil comprehensive moving end-wall surface current autocontrol system the most according to claim 1, it is characterised in that institute
The leading edge stating leading edge moving end-wall surface current autocontrol system is concordant with false wing panel leading edge, and leading edge rotating shaft (7) radius is 0.05
Times chord length.
A kind of symmetrical airfoil comprehensive moving end-wall surface current autocontrol system the most according to claim 1, it is characterised in that institute
State the lee face spindle central of lee face moving end-wall surface current autocontrol system away from 0.52 times of chord length of leading edge, away from symmetrical airfoil
0.036 times of chord length of the plane of symmetry, lee face shaft radius is 0.036 times of chord length.
A kind of symmetrical airfoil comprehensive moving end-wall surface current autocontrol system the most according to claim 1, it is characterised in that when
The wall linear velocity of leading edge moving end-wall surface current autocontrol system or lee face moving end-wall surface current autocontrol system more than or etc.
When the twice of speed of incoming flow, system can delay symmetrical airfoil stall.
A kind of symmetrical airfoil comprehensive moving end-wall surface current autocontrol system the most according to claim 1, it is characterised in that institute
The balance stated is five component aerodynamic strain balances, and balance measurement end is connected with symmetrical airfoil measuring section, sky
Under flat strut ends wing panel, symmetrical airfoil false with on symmetrical airfoil respectively, false wing panel is connected, the measurement end of balance and propping up
Rod end is not joined directly together, right ensureing on symmetrical airfoil under false wing panel and symmetrical airfoil that the power of false wing panel is not transmitted to
The two-dimensional flow of symmetrical airfoil is can guarantee that, it is possible to realize symmetrical airfoil measuring section five points while claiming on aerofoil profile measuring section
Amount aerodynamic load is measured.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410765737.2A CN104527965B (en) | 2014-11-28 | 2014-11-28 | Symmetrical airfoil comprehensive moving end-wall surface current autocontrol system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410765737.2A CN104527965B (en) | 2014-11-28 | 2014-11-28 | Symmetrical airfoil comprehensive moving end-wall surface current autocontrol system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104527965A CN104527965A (en) | 2015-04-22 |
| CN104527965B true CN104527965B (en) | 2016-08-24 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7290738B1 (en) * | 2004-10-28 | 2007-11-06 | The United States Of America As Represented By The Secretary Of The Navy | Dual jet emerging lift augmentation system for airfoils and hydrofoils |
| CN101348170A (en) * | 2008-09-01 | 2009-01-21 | 北京航空航天大学 | Wing structure having lamellar flow flowing control and separation control |
| CN102009744A (en) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | Blow/suction control method of flow separation on control surface of airplane |
| CN102390525A (en) * | 2011-10-20 | 2012-03-28 | 南京航空航天大学 | Large attack angle asymmetric vortex/lateral force closed-loop active control device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014172481A1 (en) * | 2013-04-16 | 2014-10-23 | E-Win Corporation | Fluid interface devices as well as apparatuses and methods including same |
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2014
- 2014-11-28 CN CN201410765737.2A patent/CN104527965B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7290738B1 (en) * | 2004-10-28 | 2007-11-06 | The United States Of America As Represented By The Secretary Of The Navy | Dual jet emerging lift augmentation system for airfoils and hydrofoils |
| CN101348170A (en) * | 2008-09-01 | 2009-01-21 | 北京航空航天大学 | Wing structure having lamellar flow flowing control and separation control |
| CN102009744A (en) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | Blow/suction control method of flow separation on control surface of airplane |
| CN102390525A (en) * | 2011-10-20 | 2012-03-28 | 南京航空航天大学 | Large attack angle asymmetric vortex/lateral force closed-loop active control device |
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| Publication number | Publication date |
|---|---|
| CN104527965A (en) | 2015-04-22 |
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