CN104494809A - Low wake flow wing - Google Patents
Low wake flow wing Download PDFInfo
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- CN104494809A CN104494809A CN201510016006.2A CN201510016006A CN104494809A CN 104494809 A CN104494809 A CN 104494809A CN 201510016006 A CN201510016006 A CN 201510016006A CN 104494809 A CN104494809 A CN 104494809A
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- wing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Abstract
A low wake flow wing relates to aircraft wings. The low wake flow wing is provided with a left main wing and a right main wing which are fixed to the middle portion of an aircraft body. The left portion of the left main wing extends outside to form a left flap along the rear edge of the left main wing. The right portion of the right main wing extends outside to form a right flap along the rear edge of the right main wing. A left horizontal tail and a right horizontal tail are respectively mounted on both sides of a vertical tail on the rear portion of the aircraft body. The left main wing and the right main wing are in the same width and shape. The left flap and the right flap are in the same shape and width. The width of the left flap and the right flap is 35% to 65% of that of the left main wing and the right main wing. The left horizontal tail and the right horizontal tail are in the same shape and width. The width of the left horizontal tail and the right horizontal tail is 35% to 65% of that of the left main wing and the right main wing. The distance from the edges parallel to the axis of the aircraft body, of the left flap and the right flap to the tips of the left horizontal tail and the right horizontal tail is 0% to 10% of the width of the left main wing and the right main wing. The left flap and the right flap are triangular, are connected to the rear edges of the main wings on one side and are parallel to the axis of the aircraft body on the other side respectively.
Description
Technical field
The present invention relates to a kind of aircraft wing, especially relate to a kind of low wake flow wing.
Background technology
Aircraft wake (also claiming Aircraft Training Vortices, wingtip vortex), being that the vortex sheet come off by trailing edge is formed around wing tip winding, is that wing is at the intrinsic aerodynamic phenomenon producing the association of lift while institute.Therefore, every frame aircarrier aircraft all can produce the contrary wake flow in a pair equal and opposite in direction, direction at wing rear, its concentration of energy, natural dissipation required time longer (for heavy machine, being generally more than 2 minutes).When follow-up aircraft is strayed into the wake zone of aircraft above, the lighter there will be fuselage shake, sink or face upward, moment flight attitude change, heavy then cause flying height moment significantly to change, even, will there is aircraft accident if mishandling in the phenomenon such as fuselage upset.Although the wake flow that aircraft produces can be subject to the impact of ambient windstream or the shearing stress of wake flow inside, and dribbles, this still threatens flight safety, result in the generation of some airplane crashes.
In order to eliminate the aviation safety hidden danger occurred because meeting with wake flow, International Civil Aviation Organization, US Federal Aviation Administration, C. A. A. etc. have formulated corresponding wake forcing standard, avoid rear machine to enter into the tail flow field of front machine.Enabling of this standard, effect is in early days obviously, largely prevent the accident caused by wake flow and occurs.But since entering 21 century, along with the growth at full speed of air traffic transportation volume, the introducing of wake forcing standard limits the raising of airport transport power, and airport starts to become more and more crowded.The situation that a large amount of aircraft queuings is taken off, land is of common occurrence, causes the huge energy and waste of time, seriously constrains the development of air-transport industry.
Although a lot of external factor can cause breaking of vortex, at field of fluid mechanics, the method being hopeful dissipation aircraft wake is most the fugitiveness utilizing aircraft wake.From 1970, foreign scholar made in-depth study to Crow instability, and find that, under this instable effect, the sinusoidal fluctuation of wake flow can amplify, final two wake flows are broken into many collar vortexs.But this process prescription is that naturally dissipating of wake flow is machine-processed, and its required time that breaks is longer, and uncomfortable incompatible ACTIVE CONTROL aircraft wake dissipates rapidly.
US Patent No. 6082679 discloses a kind of wing structure for ACTIVE CONTROL aircraft wake and control method thereof, is mainly used in building four vortex system systems in the same way, realizes the rapid dispersion of wake flow.
The quadrangle aileron that conventional wing configurations adopt and wing flap, its main function is the horizontal Roll control and the increase airplane ascensional force that realize aircraft, although in use these structures also can produce some vortexs, but owing to not considering its dissipation role to wingtip vortex at the beginning of design, thus effectively cannot excite the fugitiveness of wingtip vortex, realize its rapid dispersion; And the aircraft tail of routine mainly improves the fore-and-aft stability of aircraft, the relative main wing of its spanwise extent design is shorter usually, and its reverse little whirlpool produced also effectively cannot realize the dissipation of wake flow.
Summary of the invention
The object of the present invention is to provide the aerodynamic arrangement of the Aircraft Training Vortices that can initiatively dissipate, be intended to shorten wake forcing standard, improve the low wake flow wing of one of airliner flight safety.
The present invention is provided with left side main wing and right side main wing, left side main wing and right side main wing are fixed on waist position, left side main wing and right side main wing produce left side wingtip vortex and right side wingtip vortex respectively in flight course, and equal and opposite in direction, the hand of rotation of left side wingtip vortex and right side wingtip vortex are contrary; At the left part of left side main wing, stretch out left side wing flap along main wing trailing edge, left side wing flap produces the little whirlpool of wing flap, left side; At the right part of right side main wing, stretch out right side wing flap along main wing trailing edge, right side wing flap produces the little whirlpool of wing flap, right side; In the vertical tail both sides of afterbody, install left side tailplane and right side tailplane, left side tailplane and right side tailplane produce the little whirlpool of empennage, left side and the little whirlpool of right side empennage respectively;
Left side main wing is equal with right side main wing width, shape is consistent; Left side wing flap is consistent with right side wing flap shape, and width is equal, and the width of left side wing flap is 35% ~ 65% of left side main wing width; The width of right side wing flap is 35% ~ 65% of right side main wing width; Left side tailplane is consistent with right side tailplane shape, and width is equal, and the width of left side tailplane is 35% ~ 65% of left side main wing width, and the width of right side tailplane is 35% ~ 65% of right side main wing width; The limit that left side wing flap is parallel to fuselage axis is 0% ~ 10% of left side main wing width to the distance between the tailplane wing tip of left side, and the limit that right side wing flap is parallel to fuselage axis is 0% ~ 10% of right side main wing width to the distance between the tailplane wing tip of right side; Left side wing flap and right side flap configuration triangular in shape, a leg-of-mutton limit is connected with main wing trailing edge, and the diagonal angle on this limit should meet angle is 80 ° ~ 100 °; Leg-of-mutton Article 2 limit and fuselage axis line parallel, and stretch out without wingflap mechanism in space between this limit and fuselage.
Described left side wing flap is fixed on pivot, and pivot is driven by the hydraulic efficiency pressure system of main wing inside, left side, realizes the rotation around Pivot Point Center.
When left side, wing flap rotates up certain angle, when right side dirty rotates to an angle, can realize the inclination of aircraft cw (looking over along heading) certain angle; When left side, dirty rotates to an angle, and when right side wing flap rotates up certain angle, can realize the inclination of aircraft conter clockwise (looking over along heading) certain angle; When left side wing flap and right side dirty rotate equal angular, the lift of aircraft can be improved.The little whirlpool that a pair hand of rotation is contrary can be produced simultaneously, form reverse four vortex systems with wingtip vortex and unite, realize the rapid dispersion of wake flow.
The present invention gives a kind of aerodynamic arrangement of the Aircraft Training Vortices that can initiatively dissipate, be intended to shorten wake forcing standard, improve the flight safety of airliner.
Core of the present invention is that aircraft is taking off with in descent, can produce a pair contrary with direction, main whirlpool, the little whirlpool that intensity is less, construct together with wake flow one reverse four vortex systems system, in order to excite the Rayleigh-Ludwieg fugitiveness of wake flow, make wake flow rapid dispersion.
Outstanding technique effect of the present invention is:
1. adopt leg-of-mutton novel wing flap to replace conventional quadrangle aircraft aileron, the feature of the novel wing flap of this triangle is: a limit is parallel with the heading of aircraft, article one, limit is connected with trailing edge, Article 3 limit is vertical with airframe, and the length on Article 3 limit is 35% ~ 65% of wing length.
2. this novel wing flap is installed near wing tip place on the left of aircraft wing, and without other outstanding structure between this wing flap to airframe.
3. this novel wing flap can rotate around the pivot being parallel to trailing edge, and the transverse direction that can be used for controlling aircraft rolls and improves airplane ascensional force.
4. proper extension aircraft tailplane, makes empennage span be 35% ~ 65% of the main wing span, reaches and effectively can excite the instable condition of wake flow Rayleigh-Ludwieg.
Accompanying drawing explanation
Fig. 1 is the structure composition of the embodiment of the present invention and low wake flow wing aerodynamic schematic layout pattern.
Fig. 2 is the A-A section drawing of Fig. 1.
Fig. 3 is the B-B section drawing of Fig. 1.
Fig. 4 is the C-C section drawing of Fig. 1.
Fig. 5 is reverse four whirlpool system schematic.
Detailed description of the invention
Following examples will the present invention is further illustrated by reference to the accompanying drawings.
As shown in figures 1-4, be fixed on the left side main wing 6 at fuselage 5 medium position place and right side main wing 7 in flight course, produce left side wingtip vortex 13 and right side wingtip vortex 16 respectively, its equal and opposite in direction, hand of rotation are contrary.At the left part of left side main wing 6, along the left side wing flap 8 that main wing trailing edge stretches out, produce the little whirlpool 14 of novel wing flap, left side; At the right part of right side main wing 7, along the right side wing flap 9 that main wing trailing edge stretches out, produce the afterbody of the little whirlpool 15. of novel wing flap, right side at fuselage 5, the both sides of vertical tail 10, left side tailplane 11 and right side tailplane 12 are installed, produce the little whirlpool of empennage 17, left side and the little whirlpool 18 of right side empennage respectively.
Relative size between above-mentioned each parts should meet: left side main wing 6 is equal with right side main wing 7 width, shape is consistent; Left side wing flap 8 is consistent with right side wing flap 9 shape, and width is equal, and is 35% ~ 65% of left side main wing 6 width; Left side tailplane 11 is consistent with right side tailplane 12 shape, and width is equal, and is 35% ~ 65% of left side main wing 6 width; The limit that left side wing flap 8 is parallel to fuselage 5 axis is 0% ~ 10% of left side main wing 6 width to the distance between left side tailplane 11 wing tip.
Left side wing flap 8 and right side wing flap 9 profile triangular in shape.Wherein a limit is connected with main wing trailing edge, and the diagonal angle on this limit should meet angle is 80 ° ~ 100 °; Article 2 limit and fuselage 5 axis being parallel, and stretch out without wingflap mechanism in space between this limit and fuselage 5.
The hand of rotation in left side wingtip vortex 13, the little whirlpool of right side wing flap 15 and the little whirlpool 18 of right side empennage is cw; The hand of rotation in the little whirlpool of wing flap 14, left side, right side wingtip vortex 16 and the little whirlpool 17 of left side empennage is conter clockwise.
The little whirlpool of wing flap, left side 14 and the little whirlpool of left side empennage 17 are fused to the little whirlpool 19, left side of left-hand revolution; The little whirlpool of wing flap, right side 15 and the little whirlpool of right side empennage 18 are fused to the little whirlpool 20, right side of clickwise.
Left side wingtip vortex 13, right side wingtip vortex 16, the little whirlpool 20 in little whirlpool, left side 19 and right side, constitute the reverse four vortex system systems with certain feature that the present invention relates to.
Left side wing flap 8 is fixing on the pivot shaft 21, and pivot 21 is driven by the hydraulic efficiency pressure system of left side main wing 6 inside, realizes the rotation around Pivot Point Center.When left side wing flap 8 rotates up certain angle, when right side wing flap 9 is rotated down certain angle, the inclination of aircraft cw (looking over along heading) certain angle can be realized; When left side wing flap 8 is rotated down certain angle, when right side wing flap 9 rotates up certain angle, the inclination of aircraft conter clockwise (looking over along heading) certain angle can be realized; When left side wing flap 8 and right side wing flap 9 are rotated down equal angular, the lift of aircraft can be improved.The little whirlpool that a pair hand of rotation is contrary can be produced simultaneously, form reverse four vortex systems with wingtip vortex and unite, realize the rapid dispersion of wake flow.
Rayleigh-Ludwig fugitiveness, be referred to as again crossing fugitiveness, on the reference instable basis of Crow, the less whirlpool of two other intensity (being called for short little whirlpool) is introduced in the appropriate location on two wingtip vortex sides, its hand of rotation is contrary with main whirlpool, form symmetrical reverse four vortex systems systems, in order to trigger the fugitiveness of two wingtip vortex.Under experimental conditions, due to the interference of little vortex pair wake flow, cause wake flow vortex core in 10th ~ 30 spanes to break rapidly, in 45 spanes, trailing vortex intensity (characterizing by circular rector) reduces about 40%; And for when not introducing little whirlpool, in 45 spanes of measuring, wake flow vortex core is concentrated, occur without distortion, fracture phenomena, wake strength reduced by only about 10%.By this contrast experiment, describe and build this method of Rayleigh-Ludwig fugitiveness that reverse four vortex system systems excite aircraft wake, can effectively dissipate aircraft wake, has certain using value.
Based on the wing of above design feature, by reverse for formation one four vortex system systems, as shown in Figure 5, it is characterized by:
1, left side wingtip vortex 1 is equal with right side wingtip vortex semi-finals degree, and little whirlpool, left side 2 is equal with little whirlpool 3, right side intensity, and the intensity in little whirlpool 2, left side is 10% ~ 40% (intensity circular rector characterizes) of left side wingtip vortex 1.
2, symmetrical on these reverse four whirlpool alliances, if the little whirlpool 3 in little whirlpool, left side 2 and right side is apart from being b
1, left side wingtip vortex 1 and right side wingtip vortex 4 are apart from being b
0, then b
1/ b
0be 35% ~ 65%.
3, left side wingtip vortex 1 and right side little whirlpool 3 clickwise, little whirlpool 2, left side and right side wingtip vortex 4 left-hand revolution.
The low wake flow wing of one designed by the present invention, can produce the reverse four vortex system systems with certain feature, by the favourable Rayleigh-Ludwig fugitiveness exciting wake flow, realize the rapid dispersion of aircraft wake.
Innovative point of the present invention is:
1, the present invention is based on a large amount of infrastest, have stronger engineering capabilities.
2, low wake flow wing involved in the present invention, structure is simple, is easy to realize.
3, replace aileron and wing flap with novel wing flap, taken into account the needs of aircraft lift-rising and roll unloads, achieve again the inaccessiable vortex decay effect of conventional airfoil layout simultaneously.
4, the present invention sets about from the aerodynamic arrangement of aircraft wing, build reverse four vortex system systems, for the rapid dispersion of ACTIVE CONTROL aircraft wake, the measures that this and traditional reply aircraft wake are taked (such as, introduce wake forcing standard, or planning aircraft flight route is to avoid velocity wake region) be essentially different.
A kind of wing structure for ACTIVE CONTROL aircraft wake and control method thereof disclosed in US Patent No. 6082679, be mainly used in building four vortex system systems in the same way, realize the rapid dispersion of wake flow.But the present invention shows, four vortex system systems do not have reverse four vortex system systems provided by the invention obviously in the effect in vortex decay that controls in the same way, and four vortex systems are united the architectural feature realized needed for vortex decay in the same way, the Selecting parameter narrow scope when designing, engineer applied is on the weak side.
The quadrangle aileron that conventional wing configurations adopt and wing flap, its main function is the horizontal Roll control and the increase airplane ascensional force that realize aircraft, although in use these structures also can produce some vortexs, but owing to not considering its dissipation role to wingtip vortex at the beginning of design, thus effectively cannot excite the fugitiveness of wingtip vortex, realize its rapid dispersion; And the aircraft tail of routine mainly improves the fore-and-aft stability of aircraft, the relative main wing of its spanwise extent design is shorter usually, and its reverse little whirlpool produced also effectively cannot realize the dissipation of wake flow.
Claims (2)
1. one kind low wake flow wing, it is characterized in that being provided with left side main wing and right side main wing, left side main wing and right side main wing are fixed on waist position, left side main wing and right side main wing produce left side wingtip vortex and right side wingtip vortex respectively in flight course, and equal and opposite in direction, the hand of rotation of left side wingtip vortex and right side wingtip vortex are contrary; At the left part of left side main wing, stretch out left side wing flap along main wing trailing edge, left side wing flap produces the little whirlpool of wing flap, left side; At the right part of right side main wing, stretch out right side wing flap along main wing trailing edge, right side wing flap produces the little whirlpool of wing flap, right side; In the vertical tail both sides of afterbody, install left side tailplane and right side tailplane, left side tailplane and right side tailplane produce the little whirlpool of empennage, left side and the little whirlpool of right side empennage respectively;
Left side main wing is equal with right side main wing width, shape is consistent; Left side wing flap is consistent with right side wing flap shape, and width is equal, and the width of left side wing flap is 35% ~ 65% of left side main wing width; The width of right side wing flap is 35% ~ 65% of right side main wing width; Left side tailplane is consistent with right side tailplane shape, and width is equal, and the width of left side tailplane is 35% ~ 65% of left side main wing width, and the width of right side tailplane is 35% ~ 65% of right side main wing width; The limit that left side wing flap is parallel to fuselage axis is 0% ~ 10% of left side main wing width to the distance between the tailplane wing tip of left side, and the limit that right side wing flap is parallel to fuselage axis is 0% ~ 10% of right side main wing width to the distance between the tailplane wing tip of right side; Left side wing flap and right side flap configuration triangular in shape, a leg-of-mutton limit is connected with main wing trailing edge, and the diagonal angle on this limit should meet angle is 80 ° ~ 100 °; Leg-of-mutton Article 2 limit and fuselage axis line parallel, and stretch out without wingflap mechanism in space between this limit and fuselage.
2. a kind of low wake flow wing as claimed in claim 1, it is characterized in that described left side wing flap is fixed on pivot, pivot is driven by the hydraulic efficiency pressure system of main wing inside, left side, realizes the rotation around Pivot Point Center.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510016006.2A CN104494809A (en) | 2015-01-13 | 2015-01-13 | Low wake flow wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510016006.2A CN104494809A (en) | 2015-01-13 | 2015-01-13 | Low wake flow wing |
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|---|---|
| CN104494809A true CN104494809A (en) | 2015-04-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510016006.2A Pending CN104494809A (en) | 2015-01-13 | 2015-01-13 | Low wake flow wing |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104895876A (en) * | 2015-05-22 | 2015-09-09 | 厦门大学 | Method for accelerating vortex breakdown on basis of radial instability |
| CN112810803A (en) * | 2021-02-22 | 2021-05-18 | 中国民用航空飞行学院 | Aircraft wake flow adjusting device for accelerating wingtip vortex dissipation |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000002775A2 (en) * | 1998-07-13 | 2000-01-20 | State-Owned Organization Central Aerohydrodynamic Institute Named Prof. N.E. Zhukovsky | Device for reducing the vortex trail of a high-lift wing and variants |
| DE10213122A1 (en) * | 2002-03-23 | 2003-10-02 | Gerd E A Meier | Device for destabilizing of edge and trailing vortices e.g. of flying machines, consists of triangular auxiliary or stub surface, with edge of surface lying opposite tip producing contra-rotating additional vortex |
| EP0918685B1 (en) * | 1997-06-26 | 2006-03-22 | The Boeing Company | Active system for early destruction of trailing vortices |
| CN101318551A (en) * | 2008-05-28 | 2008-12-10 | 中国航天空气动力技术研究院 | Quick wing tip vortex weakening apparatus |
-
2015
- 2015-01-13 CN CN201510016006.2A patent/CN104494809A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0918685B1 (en) * | 1997-06-26 | 2006-03-22 | The Boeing Company | Active system for early destruction of trailing vortices |
| WO2000002775A2 (en) * | 1998-07-13 | 2000-01-20 | State-Owned Organization Central Aerohydrodynamic Institute Named Prof. N.E. Zhukovsky | Device for reducing the vortex trail of a high-lift wing and variants |
| DE10213122A1 (en) * | 2002-03-23 | 2003-10-02 | Gerd E A Meier | Device for destabilizing of edge and trailing vortices e.g. of flying machines, consists of triangular auxiliary or stub surface, with edge of surface lying opposite tip producing contra-rotating additional vortex |
| CN101318551A (en) * | 2008-05-28 | 2008-12-10 | 中国航天空气动力技术研究院 | Quick wing tip vortex weakening apparatus |
Non-Patent Citations (1)
| Title |
|---|
| S.HAVERKAMP*,G.NEUWERTH,D.JACOB: "Active and passive vortex wake mitigation using control surfaces", 《AEROSPACE SCIENCE AND TECHNOLOGY》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104895876A (en) * | 2015-05-22 | 2015-09-09 | 厦门大学 | Method for accelerating vortex breakdown on basis of radial instability |
| CN112810803A (en) * | 2021-02-22 | 2021-05-18 | 中国民用航空飞行学院 | Aircraft wake flow adjusting device for accelerating wingtip vortex dissipation |
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Application publication date: 20150408 |